# TCDS 3A16: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 95 - Revised: October 20, 2022 - Product: Aircraft, Small Airplane - Certification basis: Part 23, CAR 3 - Registered aircraft: 2,883, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e3/d4/e3d4fa2e9cbd11787db8fbe0b3468fc48af3dd17bd9dfe271a9746ac5fe1acdb - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID103937462920221024133648.0001 - Page: https://openairdocs.org/tcds/3A16 ## Models (21) As the data sheet lists them. - 95 - 95-B55 - 95-C55A - D55 - 58 - 95-A55 - D55A - 95-C55 - A56TC - G58 - E95 - E55 - 95-55 - 58A - D95A - E55A - 95-B55B - 95-B55A - B95 - 56TC - B95A ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No. 95 73 73 73 65 76 76 76 76 80 65 65 86 81 90 90 85 90 95 Page No. 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 Rev. No. 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 84 Page No. 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 Rev. No. 84 84 84 84 84 84 84 89 84 84 84 81 76 81 78 82 88 88 92 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A16 Revision 95 Textron Aviation B95A D55 D95A D55A E95 E55 95-55 E55A 95-A55 56TC 95-B55 A56TC 95-B55A 58 95-B55B (T-42) 58A 95-C55 95 95-C55A B95 G58 October 20, 2022 TYPE CERTIFICATE DATA SHEET NO. 3A16 This data sheet which is part of Type Certificate No. 3A16 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record: Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016 I. Model 95, Travel Air, 4 or 5 PCLM (Normal Category), Approved June 18, 1957 Engines 2 Lycoming O-360-A1A See Item 111 for optional engines. *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural cr uising 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 150 m.p.h. (130 knots) 3A16 Rev. 95 2 I. Model 95 (cont'd) C.G. Range (Landing (+79.4) to (+83.0) at 4000 lb. Gear Extended) (+75.0) to (+83.0) at 3480 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4000 lb. No. of Seats 4 (2 at +85, 2 at +121) or 5 (2 at +85, 2 at +119, 1 at +140) when Item 603(a) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 270 lb. (+140) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lb. (+135) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capaci ty Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea +75 L & R Aux. 17 ea. 17 ea. +94 Optional Fuel System (Item 106) L & R Main 25 ea. 22 ea. +75 L & R Aux 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil Control Surface Movements Wing flaps Down 33° Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 30° Left 30° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 20° Rudder Right 25° Left 25° Elevator eligible Up 10° Down 23° TD-2, TD-103 and up (main surface in neutral) Serial Nos. Eligible TD-2 through TD-302 Required Equipment Items 1(a) and (b) or 4(a) and (b ), 101(a) and (b), 102(a), 103(a), 201, 202, 205, 206, 301, 302, 304, 401(a), (b), (c), (d) and (ee) and (gg or oo), 601 II. Model B95, Travel Air, 4 or 5 PCLM (Normal Category), Approved November 13, 1959 Engines 2 Lycoming O-360-A1A See Item 111 for optional engines. *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Rev. 95 3A16 3 II. Model B95 (cont’d) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural cr uising 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 150 m.p.h. (130 knots) C.G. Range (Landing (+80.5) to (+86.0) at 4100 lb. Gear Extended) (+75.0) to (+86.0) at 3480 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4100 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(b) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 270 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 270 lb. (+145) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 17 ea. 17 ea. +94 Optional Fuel System (Item 106) L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 34° Left 30° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 20° Rudder Right 25° Left 25° Serial Nos. Eligible TD-303 through TD-452 Required Equipment Items 1(a) and (b) or 4(a) and (b ), 101(a) and (b), 102(a), 103(a), 201, 202, 205, 206, 301(a) or (b) or (c), 302, 304, 401(e) and (ee) and (gg or oo), 601 3A16 Rev. 95 4 III. Model 95-55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved November 3, 1960 Model 95-A55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved October 9, 1961 Engines 2 Continental IO-470-L *Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2625 r.p.m. (260 hp.) Airspeed Limits Maneuvering 180 m.p.h. (156 knots) (CAS) Maximum structural cr uising 210 m.p.h. (182 knots) Never exceed 257 m.p.h. (223 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 165 m.p.h. (143 knots) C.G. Range (Landing (+79.4) to (+86.0) at 4880 lb. Gear Extended) (+74.0) to (+86.0) at 3800 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4880 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(b) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(d) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) When Item 607 installed aft of Sta. 170.00 120 lb. (+180) For weight and balance informat ion, refer to DOA Flight Manual Fuel Capacity Tank Capaci ty Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 Optional Fuel System (Item 108) L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Mode l 95-55: TC-1 through TC-190 Model 95-A55: TC-191 through TC-501 (except TC-350 and TC-371) Required Equipment Items 2(b) and (a) or (d) or 9(a) or (b) or 3(a) and (b), 101(d) and (c) or (g), 101(d) and (h) (95-A55), 102(b) or (c), 103(b), 201, 202, 205, 206, 301, 302, 304, 401(gg or oo) and (k) or (q) or (am) (95-55), 501(gg or oo) and (p) or (r) or (t) or (am) (95-A55), 601(a) or (b) or (c) (95-55), 601(b) or (c) (95-A55) Rev. 95 3A16 5 IV. Model B95A, Travel Air, 4, 5 or 6 PCLM (Normal Category), Approved March 9, 1961 Engines 2 Lycoming IO-360-B1A See Item 112 for optional e ngines for S/N TD-506 only. *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural crui sing 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 150 m.p.h. (130 knots) C.G. Range (Landing (+80.5) to (+86.0) at 4200 lb. Gear Extended) (+75.0) to (+86.0) at 3600 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4200 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(b) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(d) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 400 lb. (+145) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 40 ea. 37 ea. +75 Optional Fuel System (Item 109) L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 34° Left 30° Tabs (main surface in neutral) Aileron Fixed Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible TD-453 through TD-533 Required Equipment Items 1(a) and (b) or 4(a) and (b), 101(e) or (f), 102(a), 103(a), 201 and 202 or 203 and 204, 205, 206, 301(a) or (b) or (c), 302, 304, 401(gg or oo) and (l) or (s), 601 3A16 Rev. 95 6 V. Model D95A, Travel Air, 4, 5 or 6 PC LM (Normal Category), Approved May 17, 1963 Model E95, Travel Air, 4, 5 or 6 PCLM (Normal Category), Approved October 17, 1967 Engines 2 Lycoming IO-360-B1B *Fuel 91/96 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (180 hp.) Airspeed Limits Maneuvering 160 m.p.h. (139 knots) (CAS) Maximum structural crui sing 185 m.p.h. (161 knots) Never exceed 240 m.p.h. (208 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 166 m.p.h. (144 knots) C.G. Range (Landing (+80.5) to (+86.0) at 4200 lb. Gear Extended) (+75.0) to (+86.0) at 3600 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 4200 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +153) when Item 603(e) or (f) installed or 6 (2 at +85, 2 at +121, 2 at + 150) when Item 603(d) or (g) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 270 lb. (+ 31) Optional Equipment Rear compartment 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover 400 lb. (+145) On and forward of spar cover 200 lb. (+108) For weight and balance information, refer to DOA Flight Manual. Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 40 ea. 37 ea. +75 Optional fuel system (Item 109) L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 8 qt. ea. engine (+46) (usabl e 6 qt. ea. engine), total capacity 16 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 34° Left 30° Tabs (main surface in neutral) Aileron Fixed Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Mode l D95A: TD-534 through TD-707 Model E95: TD-708 through TD-721 Rev. 95 3A16 7 V. Model D95A, Model E95 (cont'd) Required Equipment Items 1(a) and (b) or 4(a) and (b) (D95A), 4(a) and (b) (E95), 101(g) and (i), 102(a), 103(a), 201 and 202 or 203 and 204 (D95A), 201 and 202 (E95), 205, 206, 301, 302, 304, 401(u) or (w) and (bb) and (gg or oo) (D95A), 401(dd) and (gg or oo) (E95), 601(b) or (d) VI. Model 95-B55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved September 9, 1963 Model 95-B55A, Baron, 4, 5 or 6 PCLM (Normal Category), Approved October 31, 1968 Engines 2 Continental IO-470-L *Fuel 100/130 minimum grade aviation gasoline Engine Limits For airplanes prior to TC-2285 For all operations, 2625 r.p.m. (260 hp.) For airplanes TC-2285 and after Takeoff and continuous power 2625 r.p.m. (260 hp.) Normal operating power 2550 r.p.m. (252 hp.) (CAS) (IAS) Airspeed Limits Maneuvering 180 m.p.h. (156 knots) 157 knots Maximum structural cruising 210 m.p.h. (182 knots) 183 knots Never exceed 257 m.p.h. (223 knots) 224 knots Flaps extended 15° (S/N TC-2003 and up) 153 knots 28° (See NOTE 3) 130 m.p.h. (113 knots) or 140 m.p.h. (122 knots) 122 knots Landing gear extended 165 m.p.h. (143 knots) or (S/N TC-1157 and up) 175 m.p.h. (152 knots) 153 knots C.G. Range (Landing (+81.0) to (+86.0) at 5100 lb. (See NOTE 3) Gear Extended) (+80.0) to (+86.0) at 5000 lb. (+79.9) to (+86.0) at 4990 lb. (See NOTE 5) (+77.5) to (+86.0) at 4740 lb. (See NOTE 3) (+74.0) to (+86.0) at 3800 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5000 lb. or 5100 lb. (See NOTE 3) or 4990 lb. (See NOTE 5) No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(c), (f) or (j) or (m) installed or 6 (2 at +85, 2 at +121, 2 at +150) wh en Item 603(d), (g) or (k) or (n) installed Maximum Baggage and/or Forward compartmen t (above floorboard) 270 or 300 lb. (+ 31) Optional Equipment (See NOTE 3) (Structural Limits) Rear compartmen t (aft to Sta. 170.00) 400 lb. (+150) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) When Item 607 installed aft of Sta. 170.00 120 lb. (+180) For weight and balance information, refer to DOA Flight Manual. 3A16 Rev. 95 8 VI. Model 95-B55, Model 95-B55A (cont'd) Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 Optional Fuel System (Item 108) L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 S/N TC-371, TC-502 through TC-1607 Two leading edge 53 ea. wing 50 ea. wing +75 interconnected tanks with full fuel only in each wing Optional fuel system (Item 116) One leading edge 71 ea. wing 68 ea. wing +82 tanks interconnected with full fuel only with one box section tank in each wing S/N TC-1608 and up Optional fuel system (Item 118) One leading edge 71 ea. wing 68 ea. wing +82 tank interconnected with full fuel only with one box section tank in each wing S/N TC-1475 through TC-1480, TC-1575, TC-1579, TC-1584, TC-1587, TC-1593 only See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil. Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible TC-371; TC-502 a nd on, except TC-1393, TC-1394, TC-1395, TC-1396 and TC-1402. (TC-955 and on, see NOTE 3) Required Equipment Items 2(b) and (d) or (e) or 9(a) or (b), 101(d) and (h) or (l), 102(c), 103(b), 201, 202, 205, 206, 301, 302, 304, 401(v) and (gg or oo) or 401(x) and (gg or oo) or 401(ac) or 401(an), or 401(ab) and (gg or oo) or 401(ad) or 401(an), or 401(z) and (gg or oo) or 401(ae) or 401(an), or 401(hh) and (oo) or 401(af) or 401(an) (95-B55), or 401(kk) and (oo) or 401(ag) or 401(an) (95-B55A), or 401(nn) and (oo) or 401(ss) or 401(an), or 401(tt) or 401(al), or 401(ah) (95-B55, 95-B55A), 601(b) or (c) VII. Model 95-B55B, Baron, (Military T-42A), 4 PCLM (Normal or Utility Category), Approved August 26, 1964 Engines 2 Continental IO-470-L *Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2625 r.p.m. (260 hp.) Rev. 95 3A16 9 VII. Model 95-B55B (cont'd) Airspeed Limits Maneuvering 180 m.p.h. (156 knots) (CAS) Maximum structural crui sing 210 m.p.h. (182 knots) Never exceed 257 m.p.h. (223 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 165 m.p.h. (143 knots) C.G. Range (Landing (+81.0) to (+83.5) at 5100 lb. (Utility category) Gear Extended) (+81.0) to (+86. 0) at 5100 lb. (Normal category) (+77.5) to (+83.5) at 4740 lb. (Utility category) (+77.5) to (+86.0) at 4740 lb. (Normal category) (+74.0) to (+83.5) at 3800 lb . or less (Utility category) (+74.0) to (+86.0) at 3800 lb. or less (Normal category) Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5100 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(f) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(g) installed Maximum Baggage and/or Forward compartmen t (above floorboard) 270 or 300 lb. (+ 31) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) For weight and balance information, refer to DOA Flight Manual Fuel Capacity Tank Capacity Gal. Usable Gal. Arm L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil Control Surface Wing flaps Down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible TF-1 and up. Prior to civil certif ication, 95-B55B airplanes that have been operated by the military must be modified by Beech Dwg. 96-002000. Required Equipment Items 2(b) and (d) or (e) or 9(a) or (b), 101(j) and (k) or (l), 102(c), 103(b), 201, 202, 205, 206, 301, 302, 304, 401(y) and (oo), 601(b) 3A16 Rev. 95 10 VIII. Model 95-C55, Baron, 4, 5 or 6 PCLM (Normal Category), Approved August 18, 1965 Model D55, Baron, 4, 5 or 6 PCLM (N ormal Category), Approved October 17, 1967 Model 95-C55A, Baron, 4, 5 or 6 PCLM (Normal Category), Approved October 31, 1968 Model D55A, Baron, 4, 5 or 6 PCLM (N ormal Category), Approved October 31, 1968 Model E55, Baron, 4, 5 or 6 PCLM (N ormal Category), Approved November 12, 1969 Model E55A, Baron, 4, 5 or 6 PCLM (Normal Category), Approved June 16, 1970 Engines Continental IO-520-C or IO-520-CB Two of either or one of each *Fuel 100/130 minimum grade aviation gasoline Engine Limits For airplanes prior to TE-1171 For all operations, 2700 r.p.m. (285 hp.) For airplanes TE-1171 and after with 2-bladed propellers Takeoff and continuous power 2700 r.p.m. (285 hp.) Normal operating power 2550 r.p.m. (276 hp.) For airplanes TE-1171 and after with 3-bladed propellers Takeoff and continuous power 2700 r.p.m. (285 hp.) Normal operating power 2650 r.p.m. (283 hp.) Airspeed Limits (CAS) (IAS) Maneuvering 180 m.p.h. (156 knots) 156 knots Maximum structural cruising 225 m.p.h. (195 knots) 195 knots Never exceed 257 m.p.h. (223 knots) 223 knots Flaps extended 15° 175 m.p.h. (152 knots) 152 knots 28° 140 m.p.h. (122 knots) 122 knots Landing gear extended 165 m.p.h. (143 knots) or (S/N TE-633 and up) 175 m.p.h. (152 knots) 152 knots C.G. Range (Landing (+78.0) to (+86.0) at 5300 lb. Gear Extended) (+76.9) to (+86.0) at 4990 lb. (See NOTE 5) (+74.0) to (+86.0) at 4200 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5300 lb. or 4990 lb. (See NOTE 5) No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(f) or (j) or (m) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(g) or (k) or (n) installed Maximum Baggage and/or Forward compar tment (above floorboard) 300 lb. (+ 25) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) Aft baggage compartment 120 lb. (+180) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) Pneumatic Pump Limits For airplanes TE-1084 thr ough TE-1201 equipped with Beech Kit 55-5019, pneumatic pumps are time limited for engine operation to 600 hours for flight into icing conditions. Rev. 95 3A16 11 VIII. Model 95-C55, Model D55, Model 95-C55A, Model D55A, Model E55, Model E55A (cont'd) Fuel Capacity Tank Capaci ty Gal. Usable Gal. Arm L & R Main 25 ea. 22 ea. +75 L & R Aux. 31 ea. 31 ea. +93 Optional fuel system (Item 108) L & R Main 40 ea. 37 ea. +75 L & R Aux. 31 ea. 31 ea. +93 S/N TC-350, TE-1 through TE-942, except TE-938 Two leading edge 53 ea. wing 50 ea. wing +75 interconnected tanks with full fuel only in each wing Tank Capacity Gal. Usable Gal. Arm Optional fuel system (Item 116) One leading edge 71 ea. wing 68 ea. wing +82 tank interconnected with full fuel only with one box section tank in each wing Op tional fuel system (Item 114) Two leading edge 86 ea. wing 83 ea. wing +83 tanks and one box with full fuel only section tank in each wing, all tanks interconnected S/N TE-938, TE-943 and on See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil. Control Surface Wing flap Approach 15° Full down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Model 95-C55 and 95-C 55A: TC 350, TE-1 through TE-451, except TE-50 Model D55 and D55A: TE-452 through TE-767 Model E55 and E55A: TE-768 and on Required Equipment Items 2(f) and (e) or 5(a) or 10(a) or (b), 101(l) and (m) on IO-520-C engines or 101(l) and (q) on IO-520-CB engines, 102(d), 103(c) or (e), 201(e), 202(a), 205(f), 206(a), 301(i) and 304(b) (95-C55, 95-C55A, D55, D55A) or 301(m) or (q), 302(d), 401(aa) and (gg) or (oo) or 401(ar) (95-C55) or 401(ll) and (oo) or 401(ar) (95-C55A), or 401(cc) and (gg) or (oo) or 401(jj) and (oo) or 401(ar) (D55) or 401(mm) and (oo) or 401(ar) (D55A), or 401(pp) or 401(uu) or 401(aj) or 401(ar) or 401(as) (E55, E55A), or 405(a) (E55), or 405(d) (E55A), 601(b) or (c) Instrument Markings See NOTE 2(q). For airplane serial s not included, refer to the Airplane Flight Manual. 3A16 Rev. 95 12 IX. Model 56TC, Turbo Baron, 4, 5 or 6 PC LM (Normal Category), Approved May 19, 1967 Model A56TC, Turbo Baron, 4, 5 or 6 PCLM (Normal Category), Approved November 12, 1969 Engines 2 Lycoming TIO-541-E1B4 *Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2900 r.p.m. (380 hp.) 41.5 in. Hg MP Airspeed Limits Maneuvering 183 m.p.h. (159 knots) (CAS) Max. structural cruising (S.L. to 20,000 ft. alt.) 233 m.p.h. (202 knots) Max. structural cruising (25,000 ft. alt.) 222 m.p.h. (193 knots) Max. structural cruising (30,000 ft. alt.) 214 m.p.h. (186 knots) Never exceed (S.L. to 20,000 ft . alt.) 262 m.p.h. (227 knots) Never exceed (25,000 ft. alt.) 249 m.p.h. (216 knots) Never exceed (30,000 ft. alt.) 240 m.p.h. (208 knots) Flaps extended 15° 175 m.p.h. (152 knots) 28° 144 m.p.h. (125 knots) Landing gear extended 165 m.p.h. (143 knots) or (S/N TG-72 and up) 175 m.p.h. (152 knots) C.G. Range (Landing (+78.0) to (+84.2) at 5990 lb. Gear Extended) (+71.0) to (+84.2) at 4880 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5990 lb. No. of Seats 4 (2 at +85, 2 at +121 or +136) or 5 (2 at +85, 2 at +121, 1 at +150) when Item 603(f), (h) or (j) installed or 6 (2 at +85, 2 at +121, 2 at +150) when Item 603(g), (i) or (k) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 300 lb. (+ 25) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) Aft baggage compartment 120 lb. (+180) With rear seat removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) Fuel Capacity Item 113 (1) (2) Tank Capacity Gal. Usab le Gal. Usable Gal. Arm Unbaffled (Inter- 91 ea. 89 ea. 82 ea. +85 connected tank with full fuel only system, each wing) TG-2 through TG-68 or Baffled (Inter- 91 ea. 89 ea. 88 ea. +85 connected tank with full fuel only system, each wing) TG-2 through TG-68 Unbaffled (Inter- 103.5 ea. 102 ea. 94 ea. +84 connected tank with full fuel only system, each wing) TG-69 and on or Baffled (Inter- 103.5 ea. 102 ea. 101 ea. +84 connected tank with full fuel only system, each wing) TG-69 and on (1) Prior to compliance with S.I. 0559-281, Rev. 1 Rev. 95 3A16 13 IX. Model 56TC, Model A56TC (cont'd) Fuel Capacity (cont’d) (2) After co mpliance with S.I. 0559-281, Rev. 1 (S.I. - Fuel system - Es tablish minimum fuel for takeoff and increase amount of unusable fuel) See NOTE 1 for data on unusable fuel. Oil Capacity 13 qt. ea. engine (+ 35) (includes 4.7 lb. unusable ea. engine), total capacity 26 qt. See NOTE 1 for data on system oil Control Surface Wing flaps Approach 15° Full down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 33° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Model 56TC: TG-2 through TG-83 Model A56TC: TG-84 through TG-94 Required Equipment Item 6(a) and (b), 101(n) and (o), 102(e), 103(d), 201(g), 202(c), 205(f), 206(a), 301, 302(g), 304(c), 405(b) (A56TC), 601(d) or (e) or (f) or (g) Instrument Markings See NOTE 2(q) for the M odel A56TC. Refer to the Owner's Manual for the Model 56TC. X. Model 58, Baron, 4, 5 or 6 PCLM (N ormal Category), Approved November 19, 1969 Model 58A, Baron, 4, 5 or 6 PCLM (Nor mal Category), Approved November 10, 1970 Engines S/N TH-1 through TH-1395 except TH-1389 Continental IO-520C or IO-520-CB Two of either or one of each S/N TH-1389, TH-1396 through TH-2124 2 Continental IO-550-C Fuel 100/130 minimum grade aviation gasoline Engine Limits For airplanes prior to S/N TH-1090 For all operations, 2700 r.p.m. (285 hp.) For airplanes S/N TH-1090 through TH -2124 with 2-bladed propellers Takeoff and continuous power 2700 r.p.m. (285 hp.) Normal operating power 2550 r.p.m. (276 hp.) For airplanes S/N TH-1090 through TH-1395 except TH-1389 with 3-bladed propellers, takeoff and continuous power 2700 r.p.m. (285 hp.) Normal operating power 2650 r.p.m. (283 hp.) For airplanes S/N TH-1389, TH-1396 through TH-2124, all operations 2700 r.p.m. (300 hp.) Airspeed Limits (CAS) (IAS) Maneuvering 180 m.p.h. (156 knots) 156 knots Maximum structural cruising 225 m.p.h. (195 knots) 195 knots Never exceed 257 m.p.h. (223 knots) 223 knots Flaps extended 15° 175 m.p.h. (152 knots) 152 knots 30° 140 m.p.h. (122 knots) 122 knots Landing gear extended 175 m. p.h. (152 knots) 152 knots 3A16 Rev. 95 14 X. Model 58, Model 58A (cont'd) Pneumatic Pump Limits For airplanes S/N TH- 1472 through TH-1475, TH-1477 through TH-1486, TH-1488, TH-1490 and TH-1497, TH-1499 through TH-2124, and all other airplanes equipped with Beech Kit Dwg. 58-5012 pneumatic pumps are time limited for engine operation to 600 hours for flight into icing conditions. C.G. Range (Landing Model 58: S/N TH-1 through TH-1395 except TH-1389 Gear Extended) (+78.0) to (+86.0) at 5400 lb. Model 58: S/N TH-1389, TH-1396 through TH-2124 and after (+78.3) to (+86.0) at 5500 lb. for takeoff (+78.0) to (+86.0) at 5400 lb. for landing Model 58A: (+76.6) to (+86.0) at 4990 lb. Models 58 and 58A: (+74.0) to (+86.0) at 4200 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight Model 58: S/N TH-1 th rough TH-1395 except TH-1389 5400 lb. Model 58: S/N TH-1389, TH-1396 through TH-2124 5500 lb. for takeoff 5400 lb. for landing Model 58A: 4990 lb. No. of Seats 4 (2 at +75, 2 at +117) or 5 (2 at +75, 2 at +117, 1 at +150) when Item 603(j) installed or 6 (2 at +75, 2 at +117, 2 at +150) when Item 603(k) installed Maximum Baggage and/or Forward compartm ent (above floorboard) 300 lb. (+ 15) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) Aft baggage compartment 120 lb. (+180) With third and fourth seats removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) Fuel Capacity Tank Capacity Ga l. Usable Gal. Arm Baffled or 71 ea. 68 ea. +82 reservoir inter- (With full connected tank fuel only) system, ea. wing or Optional Item 114 Baffled or 86 ea. 83 ea. +83 reservoir inter- (With full connected tank fuel only) system, ea. wing or Optional Item 117 Baffled or 100 ea. 97 ea. +84 reservoir inter- (With full connected tank fuel only) system with wet wing tip ea. wing See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil Rev. 95 3A16 15 X. Model 58, Model 58A (cont'd) Control Surface Wing flaps Approach 15° Full down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Model 58/58A: TH-1 through TH-2124 SEE NOTE 17. Required Equipment For airplanes S/N TH-1 through TH-1395 except TH-1389: Items 2(f) and 7(a) or 8(a) or 11(a) or (b), 101(m) and (p) on IO-520-C engines or 101(p) and (q) on the IO-520-CB engines, 102(d), 103(c) or (e), 201(e), 202(a), 205(f), 206(a), 301(m) or (q), 302(d), 401(rr), or 401(vv), or 401(ak) (58, 58A) or 405(c) (58) or 405(e) (58A), 601(f) or (g) For airplanes S/N TH-1389, TH-1396 through TH-2124: Items 13(a) and 13(b), 101(r) and 101(s), 102(f), 103(e), 104(i), 105(d), 201(e), 202(a), 205(f), 206(a), 301(r), 302(e), 401(ap) or (aq), 601(f) or (g) Instrument Markings See NOTE 2(q). For airplane serial s not included, refer to the Airplane Flight Manual. XI. Model G58, Baron, 6 PCLM (Normal Category), Approved December 2, 2005 Engines 2 Continental IO-550-C Fuel Aviation gasoline grade 100LL or 100 minimum, and Chinese aviation gasoline RH- 95/130 and RH-100/130 Engine Limits All operations 2700 r.p.m. (300 hp.) Propeller and Propeller Limits Two Hartzell PHC-J3YF-2UF/FC7391D(K)* Maximum Diameter 75 inches, Minimum Diameter 73 inches No further tolerance permitted Pitch Settings at 30 inch station Feather 80.0 ± 0.5 degrees High Pitch: 18.5 ± 1.0 degrees Low: 12.8 ± 0.2 degrees *Hartzell STC SA10551SC incorporated by reference, Beechcraft Drawing 58-0100 Or Two McCauley 3AF32C512-(X)/(X)-82NEA-5 Maximum Diameter 77 inches, Minimum Diameter 76.5 inches No further tolerance permitted Pitch Settings at 30 inch station Feather 82.4 ± 0.5 degrees Low: 15.2 ± 0.2 degrees Airspeed Limits (CAS) (CAS) (IAS) Maneuvering 180 m.p.h. (156 knots) 156 knots Maximum structural cruising 225 m.p.h. (195 knots) 195 knots Never exceed 257 m.p.h. (223 knots) 223 knots Flaps extended 15° 175 m.p.h. (152 knots) 152 knots 30° 140 m.p.h. (122 knots) 122 knots Landing gear extended 175 m. p.h. (152 knots) 152 knots 3A16 Rev. 95 16 XI. Model G58 (cont’d) Pneumatic Pump Limits Pneumatic pumps are time limited for engine operation to 600 hours for flight into icing conditions. C.G. Range (Landing (+78.3) to (+86.0) at 5500 lb. for takeoff Gear Extended) (+78.0) to (+86.0) at 5400 lb. for landing (+74.0) to (+86.0) at 4200 lb. or less Straight line variation between points given Landing gear retraction moment (+623 in.-lb.) Empty Wt. C.G. Range None Maximum Weight 5500 lb. for takeoff 5400 lb. for landing No. of Seats 6 (2 at +75, 2 at +117, 2 at +150) Maximum Baggage and/or Forward compartm ent (above floorboard) 300 lb. (+ 15) Optional Equipment Rear compartment (aft to Sta. 170.00) 400 lb. (+150) (Structural Limits) Aft baggage compartment 120 lb. (+180) With third and fourth seats removed for cargo, maximum baggage is as follows: Aft of spar cover to Sta. 170.00 400 lb. (+145) Fuel Capacity Tank Capacity Ga l. Usable Gal. Arm Baffled or 86 ea. 83 ea. +83 reservoir inter- (With full connected tank fuel only) system, ea. wing or Optional Item 117 Baffled or 100 ea. 97 ea. +84 reservoir inter- (With full connected tank fuel only) system with wet wing tip ea. wing See NOTE 1 for data on unusable fuel. Oil Capacity 12 qt. ea. engine (+43) (includes 5.5 lb. unusable), total capacity 24 qt. See NOTE 1 for data on system oil Control Surface Wing flaps Approach 15° Full down 28° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 30° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 10° Down 10° Elevator Up 10° Down 23° Rudder Right 25° Left 25° Serial Nos. Eligible Model G58: TH-2125 and On (SEE NOTE 17). Required Equipment Equipment for the Model G58 ca n be found in the Airplane Flight Manual/Pilot’s Operating Handbook (AFM/POH), P/N 58-5900 00-67 and Illustrated Parts Catalog (IPC), P/N 58-590000-19 Rev. 95 3A16 17 XI. Model G58 (cont’d) Specifications Pertinent to All Models (except G58) Datum 83.1 inches forward of jack pads on front spar Leveling Means Two external screws in bulkhead aft of baggage compartment on left side (use plumb bob). Certification Basis Part 3 of the Civil Air Regulat ions as amended to May 15, 1956, and Paragraphs 23.1385(c), 23.1387(a) and 23.1387(e) of Fede ral Aviation Regulations, Part 23, dated February 1, 1965, as amended by Amendment 23-12. Part 36 through Amendment 36-10 of the Fe deral Aviation Regulations, 95-B55 S/N TC-2285 and after, E55 S/N TE-1171 and afte r, and 58 S/N TH-1090 through TH-2124. Type Certificate No. 3A16 issued June 18, 1957, obtained by the manufacturer under delegation option procedures. Equivalent Safety Findi ngs: CAR 3.663 and CAR 3.757 for 95-B55 and 95-B55A (S/N TC-2003 and on), E55 and E55A (S/N TE-1084 and on), 58 and 58A (S/N TH-273 and up); CAR 3.387 fo r 95-B55 and 95-B55A (all serials), E55 and E55A (all serials), a nd 58 and 58A (all serials) For Models E55 and E55A, TE-1084 through TE-1201, equipped per Beech Kit Dwg. 55-5019 and Models 58 and 58A, S/N TH-1 through TH-1471, TH-1476, TH-1487, TH-1489, TH-1498 equipped per Beech Kit Dwg. 58-5012 or Models 58 and 58A, TH-1472 through TH-1475, TH-1477 through TH-1486, TH-1488, TH-1497, TH-1499 through TH-2124, equipped per Beech Dwg. 58-000059 or Beech Kit Dwg. 58-5012, compliance with ice protection has been demonstrat ed with FAR 23.775 of Amendment 23-7; 23.773, 23.929 and 23.1419 of Amendmen t 23-14; 23.1309 of Amendment 23-17; 23.1325, 23.1327, 23.1351, 23.1357 and 23. 1547(e) of Amendment 23-20; 23.1559 of Amendment 23-21; 23.1416, and 23.1583(h) of Amendment 23-23 and 25.1323(e) of FAR 25 dated February 1, 1965. Specifications Pertinent to Model G58 only Datum 83.1 inches forward of jack pads on front spar Leveling Means Two external screws in bulkhead aft of baggage compartment on left side (use plumb bob). Certification Basis Part 3 of the Civil Air Regulat ions as amended to May 15, 1956, and Paragraphs 23.1385(c), 23.1387(a) and 23.1387(e) of Fede ral Aviation Regulations, Part 23, dated February 1, 1965, as amended by Amendment 23-12. Part 36 through Amendment 36-10 of the Federal Aviation Regulations Type Certificate No. 3A16 issued December 2, 2005, obtained by the manufacturer under delegation option procedures. Equivalent Safety Findings: CAR 3.663, CAR 3.757 and CAR 3.387 Model G58 equipped per Beech Dwg. 58-000059 or Beech Kit Dwg. 58-5012, compliance with ice protection has been demonstrat ed with FAR 23.775 of Amendment 23-7; 23.773, 23.929 and 23.1419 of Amendmen t 23-14; 23.1309 of Amendment 23-17; 23.1325, 23.1327, 23.1351, 23.1357 and 23. 1547(e) of Amendment 23-20; 23.1559 of Amendment 23-21; 23.1416, and 23.1583(h) of Amendment 23-23 and 25.1323(e) of FAR 25 dated February 1, 1965. 3A16 Rev. 95 18 XI. Model G58 (cont’d) Specifications Pertinent to Model G58 only (cont’d) Additional requirements for Ga rmin G1000 avionics installation 23.303, 23.307(a), 23.601, 23.607, 23.609, 23.1367 All subparagraphs, 23.1381 All subparagraphs at original issue; 23.395(a)(1), 23.619, 23.625, 23.689(a) All subparagraphs through Amendment 23-7; 23.771(a) through Amendment 23-14; 23.685(a) through Amendment 23-17; 23.1301 All subparagraphs, 23.1327 All subparagraphs, 23.1335 All subparagraphs through Amendment 23-20; 23.1501, 23.1541(a)(b) through Amendment 23-21; 23.603 All subparagraphs, 23.605(a) through Amendment 23-23; 23.1529 through Amendment 23-26; 23.1523 All subparagraphs through Amendment 23-34; 23.1322 All subparagraphs, 23.1331 All subparagraphs, 23.1357(a)(b)(c)(d) through Amendment 23-43; 23.305(a)(b), 23.397 All subparagraphs, 23.613(a)(b)(c)(d), 23.773(a)(2), 23.1525, 23.1549(a)(b)(c) through Amendment 23-45; 23.301(a)(b)(c), 23.561(a)(b)(3), 23.611 All subparagraphs through Amendment 23-48; 23.1303(a)(b)(c)(f), 23.1307, 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii)(3)(d), 23.1311 All subparagraphs, 23.1321(a)(b)(c)(d)(e), 3.1323(a), 23.1329 All subparagraphs, 23.1351 (a)(1)(2)(i)(b)(1)(2)(3)(c)(4)(d)(1)(g), 23.1353(a)(d)(e)(h), 23.1359(c), 23.1365(a)(b)(c)(d)(e), 23.1431(a)(b)(e) through Amendment 23-49; 23.143 All subparagraphs, 23.1325(b)(1)(i)(ii)(iii)(2)(i), 23.1543(b)(c), 23.1545(a)(b)(1)(2)(3)(4)(5), 23.1553, 23.1555(a)(b)(e)(2), § 23.1563(a)(b), 23.1581(a)(b)(2)(3)(c)(f), 23.1583(h)(m)(n), 23.1585(j) through Amendment 23-50; 23.777(a)(b), 23.1337(b)(1) through Amendment 23-51; 23.1305(a)(1)(2)(3)(b)(2)(3)(i)(4)(i)(5) through Amendment 23-52. Additional requirements for Garmin G1000 avionics with ME406 ELT: 23.303, 23.307(a), 23.601, 23.607, 23.609, 23.1367 All subparagraphs, 23.1381 All subparagraphs at original issue; 23.395(a)(1), 23.619, 23.625, 23.689(a) All subparagraphs through Amendment 23-7; 23.771(a) through Amendment 23-14; 23.685(a) through Amendment 23-17; 23.1301 All subparagraphs, 23.1327 All subparagraphs, 23.1335 All subparagraphs through Amendment 23-20; 23.1501, 23.1541(a)(b) through Amendment 23-21; 23.603 All subparagraphs, 23.605(a) through Amendment 23-23; 23.1529 through Amendment 23-26; 23.1523 All subparagraphs through Amendment 23-34; 23.1322 All subparagraphs, 23.1331 All subparagraphs, 23.1357(a)(b)(c)(d) through Amendment 23-43; 23.305(a)(b), 23.397 All subparagraphs, 23.613(a)(b)(c)(d), 23.773(a)(2), 23.1525, 23.1549(a)(b)(c) through Amendment 23-45; 23.301(a)(b)(c), 23.561(a)(b)(3), 23.611 All subparagraphs through Amendment 23-48; 23.1303(a)(b)(c)(f), 23.1307, 23.1309(a)(1)(3)(b)(c)(1)(2)(i)(iii)(3)(d)(e), 23.1311 All subparagraphs, 23.1321(a)(b)(c)(d)(e), 23.1323(a), 23.1329 All subparagraphs, 23.1351 (a)(1)(2)(i)(b)(1)(2)(3)(c)(4)(d)(1)(g), 23.1353(a)(d)(e)(h), 23.1359(c), 23.1365(a)(b)(c)(d)(e), 23.1431(a)(b)(e) through Amendment 23-49; 23.143 All subparagraphs, 23.1325(b)(1)(i)(ii)(iii)(2)(i), 23.1543(b)(c), 23.1545(a)(b)(1)(2)(3)(4)(5), 23.1553, 23.1555(a)(b)(e)(2), 23.1563(a)(b), 23.1581(a)(b)(2)(3)(c)(f), 23.1583(h)(m)(n), 23.1585(j) through Amendment 23-50; 23.777(a)(b), 23.1337(b)(1) through Amendment 23-51; Special Conditions: Garmin AT STC SA01614SE included HIRF Special Condition, 23-173-SC. Rev. 95 3A16 19 XI. Model G58 (cont’d) Specifications Pertinent to Model G58 only (cont’d) Additional requirements for Garmin GI 275 avionics installation: 23.303, 23.307(a), 23.601, 23.609, 23.671, 23.1381 (a)(b) at original issue; 23.771(a) through Amendment 23-14; 23.1301, 23.1327 through Amendment 23-20; 23.1501 through Amendment 23-21; 23.603 (a)(1)(2)(b), 23.605 (a) through Amendment 23-23; 23.1529 through Amendment 23-26; 23.1523(b) through Amendment 23-34; 23.1322, 23.1331, 23.1357(a)(b)(c) through Amendment 23-43; 23.305 (a) (b), 23.613 (a)(b), 23.1525 through Amendment 23-45; 23.301 (a) (b), 23.561 (b)(3) through Amendment 23-48; 23.1303 (a)(b)(f), 23.1309(a)(1)(3)(b)(c)(1)(2)(iii)(3)(d)(e), 23.1311(a)(b), 23.1321(a)(c)(d)(e), 23.1323(a)(c), 23.1351(a)(1)(2)(i), 23.1353(h), 23.1359(c), 23.1365(a)(d)(e), 23.1431(a)(b) through Amendment 23-49; 23.1325(a)(b)(1)(2)(i), 23.1543(b)(c), 23.1545(a)(b), 23.1555(a)(b), 23.1581(a)(1)(2) through Amendment 23-50; 23.777(a)(b) through Amendment 23-51; 23.1308(a)(b)(c) through Amendment 23-57; 23.1306(a)(b) through Amendment 23-61; 23.2010, 23.2510 through Amendment 23-64. Serial Effectivity TH-2538 & After. Additional requirements for A/C Systems LLC Automatic Climate Control System installation: The following regulations at Original issue: 23.1, 23.301(a)(b)(c), 23.303, 23.305, 23.307(a), 23.561, 23.601, 23.603, 23.605, 23.607, 23.609, 23.611, 23.613, 23.619, 23.623(a), 23.625, 23.627, 23.771(a), 23.773(a)(1)(b), 23.777(a)(b), 23.831, 23.901, 23.1041, 23.1043, 23.1047, 23.1163, 23.1183, 23.1191, 23.1301(a)(1)(2)(4)(b), 23.1351(a), 23.1357(a)(d), 23.1365, 23.1431, 23.1501(a)(b), 23.1519, 23.1541, 23.1555(a), 23.1585(a). The following regulation through Amendment 23-8: 23.1529. The following regulation through Amendment 23-14: 23.1309(a)(b). The following regulation through Amendment 23-21: 23.45(a)(b)(c)(d), 23.51(a)(b), 23.65(a), 23.77(a). Production Basis Production Certificate No. 8 issued and Delegation Option Manufacturer No. DOA-230339-CE (all models authorized to issue airworthiness certificates und er delegation option provisions of Part 21 of the Federal except G58) Aviation Regulations. Production Basis Serial Numbers TH-2125 through TH-2442: (Model G58 only) Production Certificate No. 8 issued and Delegation Option Manufacturer No. DOA-230339-CE authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Serial Numbers TH-2443 through TH-2469: Manufactured under Production Certificate No. 4 by Textron Aviation Inc., under license agreement between Beechcraft Corporation, Textron Aviation Inc., and Organization Designation Authorization Manufacturer No. ODA-100129-CE (all models) authori zed to issue airworthiness certificates under delegation option provisions of Part 21of the Federal Aviation Procedures. Serial Numbers TH-2470 and On Manufactured under Production Certificate No. 4 by Textron Aviation Inc., and Organization Designation Authorization No. ODA-100129-CE authorized to issue airworthiness certificates under organization designation provisions of Part 183 of the Code of Federal Regulations. 3A16 Rev. 95 20 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Propeller and Propeller Accessories (Excepting Deicing Equipment) 1. Two Hartzell full-feathering propeller installations (a) Hubs HC-92ZK-2 with (1) Blades 8447B-12A or 8447B-12R, spinner assembly 835-6 or 835-16 or 835-30 75 lb. ea. (+ 22) or (2) Blades 8447-12A or 8447-12R, spinner assembly 835-6 or 835-16 or 835-30 Pitch settings at 30 in. sta.: low 14°, high 84° Diameter: not over 72 in., not under 70 in. (8447B-12A) and 8447-12 blades); not over 72 in., not under 71 in. (8447B-12R and 8447-12R blades) 75 lb. ea. (+ 22) and (b) Woodward propeller governor (B210195, 210240, 210300 or 210360) 3 lb. ea. (+ 52) (c) Beech unfeathering accumulator instln. (95-960011 or 95-001046) 6 lb. ea. (+ 65) 2. Two McCauley full-feathering propeller instlns. (a) Hubs 2AF36C39 with (1) Blades 788F-0, spinner assembly PD-2749 or PD-2802 Pitch settings at 30 in. sta.: low 14.6°, high 83° Diameter: not over 78 in., not under 76 in. 76 lb. ea. (+ 18) or (2) Blades 78BFM-0, spinner assembly PD-2749 or PD-2802 Pitch settings at 30 in. sta.: low 14.6°, high 83° Diameter: not over 78 in., not under 76 in. 76 lb. ea. (+ 18) X X X X X X X X X X X X X X and (b) Woodward propeller governor (210355) or (B210438) or (210666) in pairs 3 lb. ea. (+ 26) X X X X X (c) Beech unfeathering accumulator intln. per Beech Dwg. 96-960011 or 55-001067 6 lb. ea. (+ 68) X X X X X X X X X X X X X X X (d) Hubs 2AF34C55 with (1) Blades 78FF-0, spinner assembly PD-2749 or PD-2802 or D-3831 Pitch settings at 30 in. sta.: low 15.0°, high 79.0° Diameter: not over 78 in., not under 76 in. 64 lb. ea. (+ 18) X X 1 1 X 1See Note 7. **See Note 8. ***See Note 9. Rev. 95 3A16 21 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 2. Two McCauley full-feathering propeller instlns. (cont'd) (e) Hub 2AF34C55 with (1) Blades 78FF-0, spinner assembly PD-3420 or PD-3462 or PD-3404-3 Pitch settings at 30 in. sta.: low 15.0°, high 79.0° Diameter: not over 78 in., not under 76 in. 64 lb. ea. (+ 18) X X 1 1 1 1 X X X and (f) Woodward propeller governor (D210439) or (210662) in pairs 3 lb. ea. (+ 26) X X X X X X X X 3. Two McCauley full-feathering propeller installations (a) Hubs 2AF36C89 (1) Blades 78BFS-0, spinner assembly D-2749 or D-2802 Pitch settings at 30 in. sta.: low 15°, high 79° Diameter: not over 78 in., not under 76 in. 71 lb. ea. (+ 18) Airplane Flight Manual Supplement 55-590000-37 dated March 11, 1963, required. 2 2 and (b) Woodward propeller governor (210355) or (B210438) or (210666) in pairs 3 lb. ea. (+ 26) (c) Beech unfeathering accumulator instln. per Beech Dwg. 96-960011 or 55-001067 6 lb. ea. (+ 68) X X X X 4. Two Hartzell full-feathering propeller installations (a) Hubs HC-92WK-2 with (1) Blades W8447B-12A or W84478-12R spinner assembly 835-16 or 835-30 75 lb. ea. (+22) or (2) Blades W8447-12A or W8447-12R, spinner assembly 835-16 or 835-30 Pitch settings at 30 in. sta.: low 14°, high 84° Diameter: not over 72 in., not under 70 in. (blades W8447B-12A and W8447-12A); not over 72 in., not under 71 in. (blades W8447B-12R and W8447-12R) 75 lb. ea. (+ 22) and (b) Woodward propeller governor (B210195, 210240, 210300 OR 210360) 3 lb. ea. (+ 52) (c) Beech unfeathering accumulator instln. (95-960011 or 95-001046) 6 lb. ea. (+ 65) X X X X X X X X X X X X X X X 1See Note 7. **See Note 8. ***See Note 9. 2See Note 10. 3A16 Rev. 95 22 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 5. Two McCauley full-feathering propeller installations (a) Hubs 3AF32C75 with (1) Blades 82NB-6, spinner assembly PD3499 or PD3605 Pitch settings at 30 in. sta.: low 14.0° +.2°, high 81.2° min. 82 lb. ea. (+ 18) Airplane Fli ght Manual Supplement 130486 dated December 15, 1965, or October 6, 1967 (excluding E55, E55A) or low 13.5° +.2°, high 81.2° min. Airplane Fli ght Manual Supplement 130486 dated November 12, 1965, required Diameter: 76 in., no cutoff permitted. X 2 X 2 1 1 X 2 2 X 2 2 6. Two Hartzell full-feathering propeller installations (a) Hubs HC-F3YR-2 or HC-F3YR-2F or HC-F3YR-2UF (1) Blades C7479-2R or C7479B-2R or FC7479-2R or FC7479B-2R and spinner assembly C-3269 or C-3273 Pitch settings at 30 in. sta.: low 14.0° +.2°, high 81.7° +.5° Diameter: 74 in. 94 lb. ea. (+ 6) X X and (b) Woodward propeller governor 210456 3 lb. ea. (+ 16) (c) Beech unfeathering accumulator instlns. (96-960016) 7 lb. ea. (+ 58) X X X X 7. Two McCauley full-feathering propeller instlns. (a) Hubs D2AF34C30 with (1) Blades 78FFO and spinner assembly D3953 or D4046 Pitch settings at 30 in. sta.: low 15°, high 79° Diameter: not over 78 in., not under 76 in. 69 lb. ea. (+ 15) 1 1 8. Two McCauley full-feathering propeller instlns. (a) Hubs D3AF32C35 with (1) Blades 82NB-6 and spinner assembly PD4068 or PD4069 Pitch settings at 30 in. sta.: low 14.0° +.2°, high 81.2° +.3° Diameter: 76 in., no cutoff permitted 85 lb. ea. (+ 15) 1 1 9. Two Hartzell full-feathering propeller instlns. per Hartzell STC SA795CE (a) Hubs BHC-C2YF-2 CH or BHC-C2YF-2CHU or BHC-C2YF-2CHF or BHC-C2YF-2CHUF or DHC-C2YF-2CH or DHC-C2YF-2CHU or DHC-C2YF-2CHF or DHC-C2YF-2CHUF (1) Blades C8465-6 or FC8465-6 and spinner assembly C-2285-1 or C-2285-6 X X X X X 1See Note 7. **See Note 8. ***See Note 9. 2See Note 10. Rev. 95 3A16 23 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 9. Two Hartzell full-feathering propeller instlns. per Hartzell STC SA795CE (cont'd)) or (b) Hubs PHC-C3YF-2 or PHC-C3YF-2U or PHC-C3YF-2F or PHC-C3YF-2UF (1) Blades C8465-6 or FC7663-2R and spinner assembly C-3567-1 and required data: Hartzell Manual 115B or later and FAA Approved Airpla ne Flight Manual Supplement dated September 10, 1971, or later for propellers without "U" suffix hub designation or da ted February 13, 1976, or later for propelle rs with "U" suffix hub designation X X X X X X X X X X 10. Two Hartzell full-feathering propeller instlns. per Hartzell STC SA773CE (a) Hubs BHC-C2YF-2 C or BHC-C2YF-2CHF or BHC-C2YF-2CU or BHC-C2YF-2CHUF (1) Blades C8475-6 or FC8475-6 and spinner assembly C-2285-1 or C-2285-6 X X X X X X or (b) Hubs PHC-C3YF-2 or PHC-C3YF-2F or PHC-C3YF-2U or PHC-C3YF-2UF (1) Blades C7663-2R or FC7663-2R and spinner assembly C-3567-1 and required data: Hartzell Manual 115B or later and FAA Approved Airpla ne Flight Manual Supplement required dated June 1, 1971, or later in Item (a) or (b) for propellers without "U" suffix in hub designation; dated October 29, 1975, or later in Item (a) or (b) for propellers with "U" suffix in hub designation; dated March 26, 1976, or later in Item (a) for propellers with "U" suffix in hub desig- ation and C-2285-6 spinner assembly X X X X X X X X X X X X 11. Two Hartzell full-feathering propeller instlns. per Hartzell STC SA773CE (a) Hubs BHC-J2YF-2C or BHC-J2YF-2CF or BHC-J2YF-2CU or BHC-J2YF-2CUF (1) Blades C8475-6 or FC8475-6 and spinner assembly C-2285 or C-2285-1 or C-2285-6 or (b) Hubs PHC-J3YF-2 or PHC-J3YF-2F or PHC-J3YF-2U or PHC-J3YF-2UF X X X X (1) Blades C7663-2R or FC7663-2R and spinner assembly C3567 or C-3567-1 and required data: Hartzell Manual 115B or later and FAA Approved Airpla ne Flight Manual Supplement required dated April 28, 1972, or later in Items (a) or (b) for propellers without "U" suffix in hub designation; dated October 29, 1975, or later in Item (a) or (b) for propellers with "U" suffix in hub designation; dated March 26, 1976, or later in Item (a) for propellers with "U" suffix in hub designation and C-2285-6 spinner assembly X X **See Note 8. ***See Note 9. 3A16 Rev. 95 24 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 12. Two Hartzell full-feathering propeller instlns. (for use with air conditioning) per Hartzell STC SA773CE. (a) Hubs BHC-J2YF-2CF or BHC-J2YF-2CUF (1) Blades FC8475-6 and spinner assembly C-2285-5 75 lb. ea. (+ 15) or (b) Hubs PHC-J3YF-2F or PHC-J3YF-2UF (1) Blades FC7663-2R and spinner assembly C-3567-4 91 lb. ea. (+ 15) and required data: Hartzell Manual 1 15G or later and FAA Approved Airplane Flight Manual Supplement required dated March 26, 1976, or later. X X X X X X X X X X X X 13. Two McCauley full-feathering propeller instlns. (a) Hubs 3AF32C512 with (1) Blades 82NEA-5 and spinner assembly D-5309 or D-5310 (with A/C) Pitch settings at 30 in. sta.: low 15.2° +.2°, high 82.4° +.5° Diameter: not over 77 in. not under 76.5 in. 82.5 lb. ea. (+ 75) and (b) Woodward propeller governor 210662 or B210710 or A210780 or B210800 3 lb. ea. (+ 26) X X X X Engine and Engine Accessories (Fuel and Oil Systems) 101. Fuel pumps (a) Two electric booster pumps, Bendix 476411 or Beech 58-920054-9. 2 lb. ea. (+ 88) X X and (b) Two engine-driven, AC Type AH 3 lb. ea. (+ 53) or Two engine-driven AC Type JC 1 lb. ea. (+ 53) or Two engine-driven AC Type JT (Lycoming P/N 75148 or 75246) 1 lb. ea. (+ 53) or (c) Two electric booster pumps, Weldon 4032-B 3 lb. ea. (+ 89) and (d) Two engine-driven, Continental 626062-2 or 635135-3 or 638156-3A16 or 638154-9A10 or 638154-9A11 or 638154-9A15 2 lb. ea. (+ 55) X X X X X X X X X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 25 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Engine and Engine Accessories (Fuel and Oil Systems) (e) Two electric auxiliary pumps Weldon 4036A 3 lb. ea. (+ 88) (f) Two electric auxiliary pumps Dukes Astronautics 4140-00-5 3 lb. ea. (+ 88) (g) Two electric booster pumps Dukes Astronautics 4140-00 3 lb. ea. (+ 88) (h) Two electric booster pumps P/N 96-380020 or Dukes Astronautics P/N 4613-00-1 when installed per Beech Dwg. 55-9011-3 Item 401(t) required (Model 95-A55) 3 lb. ea. (+ 88) X X X X X X X X X (i) Two engine-driven AC Type JT (Lycoming P/N 73870 or 74999 or 75131 or 75247) 2 lb. ea. (+ 53) (j) Two engine-driven, Continental 626062-3 or 63135-1 2 lb. ea. (+ 55) X X X and (k) Two electric booster pumps, P/N 96-380020-3 3 lb. ea. (+ 88) (l) Two electric booster pumps, P/N 96-380020-1 or Dukes Astronautics 4404-00-1 3 lb. ea. (+ 88) and (m) Two engine-driven, Continental 630947-2 (IO-520-C engine only) or 638154-244 (IO-520-CB engine only) 2 lb. ea. (+ 55) X X X X X X X X X X X X X X X X X X (n) Two engine-driven Beech P/N 50-921560-17 or 50-389141-1 2 lb. ea. (+ 47) and (o) Two electric booster pumps, P/N 60-389010 or 60-389010-1 or -7 or -9 or -11 or Beech Kit Dwg. 60-9005 for P/N 60-389010-15 5 lb. ea. (+ 75) (p) Two electric booster pumps Dukes Astronautics 4404-00 or 4404-00-1 3 lb. ea. (+ 88) X X X X X X (q) Two engine-driven, Continental 638154-16A3 (IO-520-CB engine only) 2 lb. ea. (+ 55) (r) Two engine-driven, Continental 643536-1 (IO-520-C engine only) 3 lb. ea. (+ 55) (s) Two electric booster pumps Dukes Astronautics 4404-00-1 3 lb. ea. (+ 88) X X X X X X X X **See Note 8. ***See Note 9. 3A16 Rev. 95 26 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 102. Two oil radiators (a) Harrison 8523517 or 8526250 2 lb. ea. (+ 30) (b) Harrison 8526732 or CMC 626189 5 lb. ea. (+ 27) (c) Modine EPR2036 or CMC 630050, 637300, 635993 or 639151 9 lb. ea. (+ 27) (d) Continental 633288 or 633277 or 634063 or 635996 7 lb. ea. (+ 53) (e) Harrison 8535849 or Lycoming 77714 or 76056Y or LW10025 10 lb. ea. (+ 41) (f) Continental 635996 7 lb. ea. (+ 53) X X X X X X X X X X X X X X X X X X X X X X X X 103. Two carburetor or induction air cleaner (a) Air Maze 121128-1 1 lb. ea. (+ 35) (b) Air Maze 122601 or Donaldson P12-8219 1 lb. ea. (+ 61) (c) Air Maze 121128-2 or Donaldson P12-7996 1 lb. ea. (+ 65) (d) Beech 50-389070-7 1 lb. ea. (+ 56) (e) Beech 96-389005-1 1 lb. ea. (+ 63) (E55 and E55A. S/N TE-1079 and up) (58 and 58A, S/N TH-741 through TH-2124 (G58, S/N TH-2125 and after) X X X X X X X X X X X X X X X X X X X X X X X X X X 104. Vacuum pump and/or pressure pump (a) Pesco 3P-194FA or Garwin G450L or G455L or G455 or G455PM 3 lb. ea. (+ 50) (b) Garwin G455 or G455PM 3 lb. ea. (+ 56) (c) Airborne Mechanisms 113-A-2 4 lb. ea. (+ 50) (d) Beech 50-380090 or 50-380090-1 or 50-380090-2 5 lb. ea. (+ 56) 1 1 1 1 1 1 2 2 2 2 2 2 2 2 2 2 2 2 2 2 (e) Airborne Mechanisms 224CW or 232CW 4 lb. ea. (+ 48) or 242CW 2 lb. ea. (+ 48) or 432CW 6 lb. ea. (+ 48) or 442CW 3 lb. ea. (+ 48) 2 2 2 2 2 2 2 2 (f) Airborne Mechanisms 200CW or 232CW 4 lb. ea. (+ 56) or 242CW or 212CW or 216CW 2 lb. ea. (+ 56) or 432CW-12 6 lb. ea. (+ 56) or 442CW-12 3 lb. ea. (+ 56) (g) Airborne Mechanism 200CC 4 lb. ea. (+ 50) (h) Airborne Mechanisms 212CW or 216CW 2 lb. ea. (+ 56) or 442CW-12 or 442CW-14 3 lb. ea. (+ 56) (95-B55 and 95-B55A S/N TC-2003 and up) (i) Airborne Mechanisms 212CW or 216CW 2 lb. ea. (+ 56) or 442CW-12 3 lb. ea. (+ 56) 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 1One or two vacuum pumps 2 Two vacuum or pressure pumps **See Note 8. ***See Note 9. Rev. 95 3A16 27 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 105. Two starters (a) Lycoming 71348 or 72337 (Delco-Remy 1109687) or Lycoming 72464 (Delco-Remy 1109518) or Lycoming 72462 (Delco-Remy 1109517) or Lycoming 76212 (Prestolite MHB-4001) 18 lb. ea. (+ 31) (b) Delco-Remy 1108234 (CMC 627841) or Prestolite MHJ4002 (CMC 634433) or Prestolite MHJ4003 (CMC 637847) 16 lb. ea. (+ 55) (c) Lycoming 75700 (Prestolite MHB4002) 18 lb. ea. (+ 22) (d) Continental 646275 14.5 lb. ea. (+ 55) X X X X X X X X X X X X X X X X X X X X X X X 106. Optional fuel system 56 gal. capacity ea. wing +8 lb. (+ 91) X X 107. Heated fuel vent masts installed per Beech Dwg. 95-001034 Negligible weight X X X 108. Optional fuel system 71 gal. capacity ea. wing +11 lb. (+ 75) X X X X X X X X X X 109. Optional fuel system 56 gal. capacity ea. wing +25 lb. (+ 98) X X X 110. Winterization equipment instln. per Beech Dwg. 96-910017 or 55-001068 2 lb. (+ 24) Airplane Flight Manua l Supplement P/N 55-001069 dated December 28, 1961, required (excluding 95-B55, S/N TC-1403 and up, and 95-B55A, S/N TC-1403 and up) (a) Engine cooling air inlet baffle (b) Oil radiator air baffle (must be removed for operation at 70° F. or above O.A.T.) 1 1 1 2 2 2 2 111. Lycoming IO-360-B1A engines installed per Beech Dwg. 95-910001 Use actual weight change Airplane Flight Manual 95-590014-57 dated January 21, 1962, required in lieu of Items 402(a) or (b) or (d) Airplane Flight Ma nual 95-590014-49 dated January 5, 1961, required in lieu of Item 401(e) Item 101(e) required in lieu of Items 101(a) and (b) X X X X X 112. Lycoming IO-360-B1B engines installed per Beech Dwg. 95-910002 Use actual weight change Airplane Flight Manual 95-590014-65 dated July 29, 1963, required in lieu of Item 401(l). Item 101(g) required in lieu of 101(e) or (f) X 113. 91 gal. capacity Fuel system ea. wing +21 lb. (+ 95) or 103.5 gal. capacity Fuel system ea. wing +33 lb. (+ 88) X X X **See Note 8. ***See Note 9. 1See Note 13. 2See Note 14. 3A16 Rev. 95 28 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 114. Optional fuel system 86 gal. capacity with baffle or reservoir ea. wing +31 lb. (+ 76) +36 lb. (+ 91) X X X X X X 115. L.H. and/or R.H. main fuel tanks (22 or 37 gal. ea.) installed per Beech Dwg. 35-9009 Negligible weight X X X X X X X X X X X X X X 116. Optional fuel system 71 gal. capacity ea. wing +36 lb. (+ 91) and -31 lb. (+ 76) X X X X 117. Optional fuel system 100 gal. capacity with baffle or reservoir and wet wing tip ea. wing +50 lb. (+ 82) X X X X 118. Optional fuel system 71 gal. capacity ea. wing per Beech Dwg. 55-9015. Airplane Flight Ma nual Supplement P/N 131350 revised May 10, 1976, required (95-B55 Serials TC-1475 through TC-1480, TC-1575, TC-1579, TC-1584, TC-1587 and TC-1593). Wt. and arm are determined on each airplane. X Landing Gear 201. Two main wheel-brake assemblies, 6.50-8, Type III (a) Goodyear Wheel assembly 9531711 8 lb. ea. (+ 96) Brake assembly 9531712 5 lb. ea. (+ 97) or (b) Goodyear Wheel assembly 9532135 8 lb. ea. (+ 96) Brake assembly 9532167 5 lb. ea. (+ 97) (c) Goodyear Wheel assembly 8532135 8 lb. ea. (+ 96) Brake assembly 9532475, 9532412 or 9532679 5 lb. ea. (+ 97) X X X X X X X X X or (d) Beechcraft Wheel assembly 96-300001-3 or -51 8 lb. ea. (+ 96) Brake assembly 96-300001-5 6 lb. ea. (+ 97) or (e) Cleveland Wheel assembly 40-98 10 lb. ea. (+ 96) Brake assembly 30-66 or 30-66G 4 lb. ea. (+ 97) or (f) Cleveland For model D95A. Wheel assembly 40-98 10 lb. ea. (+ 96) Brake assembly 30-66 4 lb. ea. (+ 97) (Installed per Mod C.O. B73772-D95A only) X X X X X X X X X X X X X X X X X X X X X X X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 29 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Landing Gear 201. (cont'd) or (g) Cleveland Wheel assembly 40-98 10 lb. ea. (+ 96) Brake assembly 30-69 or 30-69 "A" 4 lb. ea. (+ 97) X X or (h) Cleveland Wheel assembly 40-128 12 lb. ea. (+ 96) Brake assembly 30-93B or 30-93C 5 lb. ea. (+ 97) X X X X X X X X 202. (a) Two main wheel 6-ply or 8-ply tires 6.50-8 with regular tubes for use with Item 201. Wheels 9532135 and 96-300001-3 to be modified per Goodyear Dwg. 5R3-123 13 lb. ea. (+ 96) or (b) Two main wheel 6-ply rating tube- less tires with side inflation to be used with Item 201(b) or (c) or (d) 12 lb. ea. (+ 96) or (c) Two main wheel 8-ply rating 6.50-8 with regular tubes for use with Item 201(g) 14 lb. ea. (+ 96) X X X X X X X X X X X X X X X X X X X X X X X X X X X X 203. Two main wheel-brake assemblies (a) Beechcraft Wheel assembly 95-300001-1, -67 or -73 Brake assembly 95-300001-5 (LH) Brake assembly 95-300001-6 (RH) 12 lb. ea. (+ 97) or (b) Cleveland For models B95A and D95A Wheel assembly 40-83 Brake assembly 30-54 9 lb. ea. (+ 97) or (c) Beechcraft For models B95A and D95A Wheel assembly 35-8002-3 4 lb. ea. (+ 96) Brake assembly 35-8002-5 7 lb. ea. (+ 96) X X X X X X 204. Two main wheel tires (a) 7.00-6, Type III, 6-ply tubeless tires with side inflation 10 lb. ea. (+ 96) or (b) 7.00-6, Type III, 6-ply rating tires with regular tubes 12 lb. ea. (+ 96) X X X X 205. One nose wheel 5.00-5, Type III (a) Wheel assembly Goodyear 9520653 3 lb. (+ 12) or (b) Wheel assembly B.F. Goodrich 3-897 3 lb. (+ 12) or (c) Wheel assembly Goodyear 9532102 4 lb. (+ 12) or (d) Wheel assembly Goodyear 9532669 4 lb. (+ 12) or (e) Wheel assembly Goodyear 9532926 4 lb. (+ 12) or (f) Wheel assembly Cleveland 40-87 3 lb. (+ 12) 3 lb. (+ 0) 3 lb. (- 10) X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X **See Note 8. ***See Note 9. 3A16 Rev. 95 30 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 206. (a) One nose wheel 6-ply rating tire 5.00-5, with regular tube for use with Item 205. Wheels 9532102 or 9532669 modified per Goodyear Dwg. 5R2-365, 5R2-366 6 lb. (+ 12) 6 lb. (+ 0) 6 lb. (- 10) or (b) One nose wheel 6-ply rating tubeless tire, 5.00-5 with side inflation to be used with Item 205(c) and (d) only 6 lb. (+ 12) X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 210. Co-pilot's brakes 4 lb. (+ 54) 4 lb. (+ 44) X X X X X X X X X X X X X X X X X X X X X X Electrical Equipment 301. Generators (a) Two 15 a. generators (Delco-Remy 1101901 or Lycoming 68765) and two 15 a. regulators (Delco-Remy 119144) 17 lb. ea. (+ 33) (b) Two 25. a. generators (Delco-Remy 1101905 or Lycoming 68871) and two 25 a. regulators (Lycoming 71350 or Delco-Remy 1118976) 22 lb. ea. (+ 35) (c) Two 40 a. generators (Delco-Remy 1105052) and two 40 a. regulators (Delco-Remy 1119237C) 26 lb. ea. (+ 33) (d) Two 25 a. generators (Delco-Remy 1101911 or CMC 627274) and two 25 a. regulators (Delco-Remy 1118976) 19 lb. ea. (+ 54) (e) Two 40 a. generators (Delco-Remy 1105053 or 1105056 or CMC 628010) and two 40 a. regulators (Delco-Remy 119237C) 26 lb. ea. (+ 54) (f) Two 50 a. generators (Delco-Remy 1105057 or CMC 629417) and two 50 a. regulators (Delco-Remy 1119656) 24 lb. ea. (+ 54) (g) Two 50 a. alternators (CMC 631111 or Delco-Remy 1100685 or 1100718 or 1100747) and two 50 a. regulators (Delco-Remy 9000591) or (Beech 60-3890017) (Overvoltage relay integral part of regulator) 13 lb. ea. (+ 54) X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X (h) Two 50 a. alternators (Lycoming 74879) and two 50 a. regulators (Delco-Remy 9000591) or (Beech 60-389017) (Overvoltage relay integral part of regulator) 13 lb. ea. (+ 33) X X (i) Two 50 a. alternators (CMC 632590) or (Delco-Remy 1100723) and two 50 a. regulators (Delco-Remy 9000591) or (Beech 60-389017) (Overvoltage relay integral part of regulator) 12 lb. ea. (+ 28) X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 31 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 301. (j) Two 60 a. alternators Beech 96- 910004-25 (Ford DOFF-1030-N) or Beech 60-389014 (F ord DOFF-10300-A) or Beech 60-389014- 1 (Ford C7FF-10300-C) 12 lb. ea. (+ 18) and two 50 a. regulators (Beech 60-389017) (Overvoltage relay integral part of regulator) 2 lb. ea. (+ 68) X X or (k) Two 125 a. generators (Lear-Siegler P/N 30060-004) 29 lb. ea. (+ 18) and two regulators (General Electric CR2795B105A1) 3 lb. ea. (+ 68) and two overvoltage relays (REM 138-5) 1 lb. ea. (+ 68) X X or (l) Two 50 a. alternators (CMC 634692) (Prestolite ALT-8403) or (CMC 640393) (Prestolite ALT-8407) or (CMC 641658) (Prestolite ALT- 8420) and two 50 a. regulators (Beech 60-389017) (Over- voltage relay integral part of regulator) 13 lb. ea. (+ 54) X X (m) Two 50 a. alternators (CMC 634445) (Prestolite ALT-9405) or (CMC 641668) (Prestolite ALT-9422) and two 50 a. regulators (Beech 60-389017) (Over- voltage relay integral part of regulator) 13 lb. ea. (+ 28) (n) Two 100 a. (Derated to 85 a.) alternators (Teledyne-Continental TCM P/N 640053, Pr estolite P/N ALV- 9401) or (TCM P/N 640789, Presto- lite P/N ALV-9407) per Beech kit Dwg. 58-3001-1 or 58-3001-7 Airplane Flight Manual Supplement P/N 131271 dated March 27, 1974 21.6 lb. ea. (+ 27) Airplane Flight Manual Supplement 96-590010-23 dated October 1976 or later required (E55 and E55A S/N TE-1084 and up) (58 and 58A S/N TH-773 through TH-2124) X X X 1 X 1 X 1 X X X 1 (o) Two optional 100 a. (Derated to 85 a.) alternators (Teledyne Continental TCM P/N 640789, Pr estolite P/N ALV- 9407)(E55 and E5A S/N TE-1122 and up)(58 and 58A S/N TH-895 and up) 22 lb. ea. (+ 28) and two regulators (Beech P/N 60-389017-3)(Overvoltage relay is an integral part of the regulator) 1 lb. ea. ( 0) 1 lb. ea. (+ 10) X X X X X X X X **See Note 8. ***See Note 9. 1See Note 11. 3A16 Rev. 95 32 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 301. (cont'd) or (p) Two optional 100 a. alternators (TCM alternator P/N 642056 or 646491 or TCM alternator and hub assembly P/N 646844 or 649305) 19 lb. ea. (+ 28) and two regulators (Beech P/N 60- 389017-3)(Overvoltage relay is an integral part of the regulator) 1 lb. ea. ( 0) 1 lb. ea. (+ 10) (q) Two 60 a. alternators (TCM alternator P/N 642055 or 646490 or TCM alternator assembly P/N 646845) 11.5 lb. (+ 28) and two regulators (Beech P/N 60-389017-3)(Overvoltage relay is an integral part of the regulator) 1 lb. ea. ( 0) 1 lb. ea. (+ 10) X X X 2 X X X X X X X X X X X (r) Two 60 amp alternators (TCM alternator P/N 646490 or TCM alternator assembly P/N 646845) 12 lb. ea. (+ 28) and two alternator controls (Beech P/N 102-384038-1)(Overvoltage relay is an integral part of the regulator) 1 lb. ea. (+ 39) (s) Two optional 100 amp alternators (TCM alternator P/N 646491 or TCM alternator and hub assembly P/N 646844 or 649305) 19 lb. ea. (+ 28) and two alternator controls (Beech P/N 102-384038-1)(Overvoltage relay is an integral part of the regulator) 1 lb. ea. (+ 39) X X X X X X X X (t) Two optional Prestolite 50 amp alternators (TCM alternator P/N 641668, Prestolite P/N ALT-9422, or TCM alternator and hub assembly P/N 641668A1) 13 lb. ea. (+ 28) and two alternator controls (Beech P/N 102-384038-1)(Overvoltage relay is an integral part of the regulator). 1 lb. ea. (+ 39) X X 302. Battery (a) One 24 v. 17 a.hr. (Gill 12-GCAB-9) 30 lb. (+ 18) 30 lb. (+ 20) 30 lb. (+ 32) or (b) Two 12 v. 24 a.hr. (Reading S24) 21 lb. ea. (+ 18) 21 lb. ea. (+ 20) 21 lb. ea. (+ 32) X X X X X X X X X X X X X X X X X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 33 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 302. Battery (cont'd) (c) Two 12 v. 24 a.hr. Nickel-Cadmium (Sonotone 22321/CA15A and 22321/CA15B) or (Sonotone/Marathon 27341-1/CA15A and 27341-2/CA15B) installed per Beech Dwg. 95-001031 or Mod. C.O. B75184. 17 lb. ea. (+ 10) 17 lb. ea. (+ 18) 17 lb. ea. (+ 20) 17 lb. ea. (+ 32) Airplane Flight Manual Supplement P/N 95-001035 dated November 20, 1959 or Rev. March 10, 1961, or later required. (Excluding 95-B55 and E55A S/N TE-880 and up, 58 and 58A S/N TH-264 through TH-2124 Battery charge current sensor installed per Beech Dwg. 60-3005 (negligible weight) and Ai rplane Flight Manual Supplement P/N 131176 dated October 1, 1973, or later required. Nickel-cadmium battery and charge current detector Airplane Flight Manual Supplement P/N 96-590010-21 dated October 1976 or later required. or (d) One 24 v. 17 a.hr. (Beech 118654) 30 lb. ea. (+ 10) 30 lb. ea. (+ 18) 30 lb. ea. (+ 20) 30 lb. ea. (+ 32) or (e) Two 12 v. 24 a.hr. Beech 118658 23 lb. ea. (+ 10) 23 lb. ea. (+ 18) 23 lb. ea. (+ 20) or 58-380056-1 (12V Lead Acid Battery) 21 lb. ea. (+ 10) 21 lb. ea. (+ 18) 21 lb. ea. (+ 20) 21 lb. ea. (+ 32) X 1 2 2 X X X X 1 2 2 X X X X 2 2 X X X X 2 2 X X X X 2 2 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 2 2 X X X X 2 2 X 1 2 2 X X X X 1 2 2 X X X X 2 2 X X X X X X X X X (f) One 24 v. 11 a.hr. Nickel-Cadmium (MS24496-1) 34 lb. ea. (+ 32) (g) One 24 v. 13 a.hr. Nickel-Cadmium (Beech 50-380078-1 or 50-380078) 31 lb. ea. (+ 75) Battery charge current sensor installed per Beech Dwg. 60-3005 (Negligible weight) and Airplane Flight Manual Supplement P/N 131172 dated October 1, 1 973, or later required. (h) Two 24 v. 13.6 a hr. Sealed Lead Acid (Concorde RG24-15) installed per Beech Dwg 58-364100. 29.5 lbs. ea (+ 10) X X X X X **See Note 8. ***See Note 9. 1See Note 10. 2See Note 11. 3A16 Rev. 95 34 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 303. Two landing lights One or two landing lights (a) General Electric 4523 or 4553 (Wing leading edge instln.) 1 lb. ea. (+ 75) (b) General Electric 4523 or 4553 (nose cone instln.) 1 lb. ea. (- 9) (c) General Electric 4553 (nose shock strut instln.) 1 lb. ea. (+ 11) (d) General Electric 4596 (wing tip instln.) 1 lb. ea. (+ 81) (e) General Electric 4596 (nose cone instln.) 1 lb. ea. (- 16) (f) General Electric 4596 (nose shock strut instln.) 1 lb. ea. (- 8) (g) General Electric (engine cowling instln. used only on aircraft with optional wet wing tip fuel) TH-874 and up 1 lb. ea. (+ 23) 304. Relay (a) Paralleling Delco-Remy 1116902 or Lycoming 71349 1 lb. ea. (+ 49) or (b) Overvoltage (Beech 50-380058-1 or Delco-Remy 1115832 or RBM-138-2) for use with Item 301(g) or (h) or (i) only when Delco-Remy 9000591 regulators are used 1 lb. ea. (+ 49) or (c) Paralleling (Beech 50-380048-1) for use with Item 301(k) only Negligible weight Interior Equipment 401. DOA Approved Airplane Flight Manual (a) Dated June 18, 1957, S/N TD-2 (b) Dated October 28, 1957, S/N TD-3 through TD-60 (c) Dated February 17, 1958, S/N TD-61 through TD-72 (d) Dated March 10, 1958, S/N TD-73 through TD-302 (e) Dated November 20, 1959, S/N TD-303 through TD-452 (k) P/N 55-590000-3 dated November 2, 1960 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 1 X X 2 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X **See Note 8. ***See Note 9. 1S/N TC-400 through TC-501. 2See Note 13. Rev. 95 3A16 35 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Interior Equipment (cont'd) 401. (l) P/N 95-590014-51 dated January 20, 1961, or October 27, 1961 (S/N TD-453 through TD-533) (p) P/N 55-590000-27 dated October 5, 1961 (S/N TC-191 through TC-420 except TC-350 and TC-371) (q) P/N 55-590000-3 dated January 25, 1963 (required with 400 lb. re ar baggage compartment and/or Item 2(d) X 3 3 (r) P/N 55-590000-27 dated January 25, 1963 (required with 400 lb. re ar baggage compartment and/or Item 2(d)) (S/N TC-191 through TC-420 except TC-350 and TC-371) (s) P/N 95-590014-51 dated November 30, 1962 (required with 400 lb. rear baggage compartment) (t) P/N 55-590000-27 dated February 27, 1963, or February 16, 1965 (required with Item 2(d) and 101(h)) (S/N TC-421 through TC-501) (required with Item 2(d), (except S/N TC-350 and TC-371) (u) P/N 95-590014-59 dated October 6, 1964 (S/N TD-534 through TD-622) (v) P/N 55-590000-43 dated September 6, 1963 (S/N TC-371, TC-502 through TC-909 except TC-846) (w) P/N 95-590014 dated January 8, 1965 (S/N TD-623 through TD-707) (x) P/N 55-590000-43 dated January 8, 1965, or February 16, 1965 (S/N TC-846, TC-910 through TC-954) (y) P/N 55-590000-49 dated July 15, 1965, or later (S/N TF-1 and up) (z) P/N 55-590000-55 dated July 15, 1965, or February 15, 1968 (S/N TC-955 through TC-1156) (aa) P/N 55-590006-3 dated June 25, 1965 (S/N TC-350, TE-1 through TE-451 except TE-50) (ab) P/N 130544 dated March 11, 1966, required if Kit 55-4014 is installed (S/N TC-371, TC-502 through TC-954) (ac) P/N 55-590000-43 dated May 7, 1975 (S/N TC-371, TC-502 through TC-954) (ad) P/N 130544 dated October 10, 1975, required if Kit 55-4014 is installed (S/N TC-371, TC-502 through TC-954) (ae) P/N 55-590000-55 dated May 7, 1975 (S/N TC-955 through TC-1156) (af) P/N 130821 dated October 4, 1974 (S/N TC-1157 through TC-1402) (ag) P/N 130835 dated October 4, 1974 (S/N TC-502 through TC-1402) (bb) Airplane Fli ght Manual Supplement P/N 95-590014-45, revised March 17, 1965, required (S/N TD-620 through TD-707) (cc) Airplane Flight Manual P/N 130738 dated October 6, 1967, or November 10, 1967 (S/N TE-452 through TE-632) (dd) Airplane Flight Manual P/N 130741 dated October 6, 1967, or November 10, 1967 (S/N TD-708 and up) 2 X X X X X 3 3 4 4 4 4 4 4 4 4 1 X 2 1See Notes 5 and 14. **See Note 8. ***See Note 9. 2See Note 10. 3See Note 13. 4See Note 14. 3A16 Rev. 95 36 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Interior Equipment (cont'd) 401. DOA Approved Airpla ne Flight Manual (cont'd) (ee) Airplane Fli ght Manual Supplement P/N 130777 dated January 9, 1968, required (ff) Airplane Fli ght Manual Supplement P/N 130793 dated March 8, 1968, required on aircraft with pressure air instrument system X X 2 (gg) Airplane Fli ght Manual Supplement P/N 130776 dated November 27, 1968 (excluding D55, S/N TE-633 through TE-767 and 95-B55, S/N TC-1157 through TC-1402) (hh) Airplane Flight Manual P/N 130821 dated December 2, 1968; August 28, 1970; January 5, 1971; or May 31, 1971 (S/N TC-1157 through TC-1402) 2 X X X X X 4 4 5 5 2 (jj) Airplane Flight Manual P/N 130820 dated December 2, 1968 (S/N TE-633 through TE-767) (kk) Airplane Flight Manual P/N 130835 dated February 6, 1970; August 25, 1970; January 5, 1971; or May 31, 1971 (S/N TC-502 through TC-1402) (ll) Airplane Flight Manual P/N 130836 dated Februiary 6, 1970, or later 2 6 3 (mm) Airplane Flight Manual P/N 130837 dated February 6, 1970, or later (nn) Airplane Flight Manual P/N 96-590011-1 dated September 3, 1971, or later (S/N TC-1403 through TC-1607) (oo) Airplane Fli ght Manual Supplement P/N 96-590011-7 dated February 11, 1972 (required with baffled fuel cells only) (excluding 95-B55 and 95-B55A, S/N TC-1403 and up) 2 3 2 X X X X X 4 4 5 5 6 5 X X X (pp) Airplane Flight Manual, P/N 96-590010-5 dated September 8, 1972, or later (S/N TE-768 through TE-942 except TE-938) (rr) Airplane Flight Manual P/N 58-590000-11 dated September 8, 1972, or la ter; or 58-590000-31B dated January, 1983 or later (S/N TH-1 through TH-384) (ss) Airplane Flight Manual P/N 96-590011-1 dated September 3, 1971, and revised to February 11, 1972, or later (S/N TC-1403 through TC-1607) 2 3 X 5 6 1 (tt) Airplane Flight Manual P/N 96-590011-11 dated September 10, 1973, or later (S/N TC-1608 through TC-2002) (uu) Airplane Flight Manual P/N 96-590010-9 dated September 10, 1973, or later (S/N TE-938, TE-943 through TE-1083) (vv) Airplane Flight Manual P/N 58-590000-15 dated September 10, 1973, or later; or 58-590000-31B dated January 1983 or later (S/N TH-385 through TH-772) 3 4 X 7 8 1 1See Note 5 4See Note 13 **See Note 8 5See Note 14 ***See Note 9 6See Notes 5 and 14 2See Note 10 7See Note 15. 3See Notes 5 and 10 8See Notes 5 and 15. Rev. 95 3A16 37 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Interior Equipment (cont'd) 401. (ah) Pilot's Operating Handbook and Airplane Flight Manual P/N 96-590011-17 dated October 1976 or late r (S/N TC-2003 and up) (aj) Pilot's Operating Handbook and Airplane Flight Manual P/N 96-590010-17 dated October 1976 or late r (S/N TE-1084 and up) (ak) Pilot's Operating Handbook and Airplane Flight Manual P/N 58-590000-21 dated October 1976 or later (S/N TH-773 through TH- 2124 (al) Pilot's Operating Handbook and Airplane Flight Manual P/N 96-590011-23 dated May 1978 or later (S/N TC-1608 through TC-2002 X 1 X X 7 1 8 1 (am) Pilot's Operating Handbook and) Airplane Flight Manual P/N 55-590000-65 dated November 1978 or later (S/N TC-1 through TC-504 except TC-350 and TC-371) (an) Pilot's Operating Handbook and Airplane Flight Manual P/N 96-590011-25 dated October 1970 or later (TC-371, TC-502 through TC-1607) 5 5 6 6 (ap) Pilot's Operating Handbook and Airplane Flight Manual P/N 58-590000-35 dated December 1983 or later (S/N TH-1389, TH-1396 through TH-1471, TH-1476, TH-1487, TH-1489 & TH-1498) X X (aq) Pilot's Operating Handbook and Airplane Flight Manual P/N 58-590000-39 dated October 1984 or later (S/N TH-1472 through TH- 2124 except TH-1476, TH-1487, TH-1489 & TH-1498). (ar) Pilot's Operating Handbook and Airplane Flight Manual P/N 96-590010-29 dated July 1979 or later (TC-150 and TE-1 through TE-942, except TE-918) (as) Pilot's Operating Handbook and Airplane Flight Manual P/N 96-590010-31 dated March 1979 or later (TE-938, TE-943 through TE-1083) 2 2 2 3 2 3 2 2 X 1See Note 5. **See Note 8. ***See Note 9. 2See Note 10. 3See Note 12. 4See Notes 5 and 12. 5See Note 13. 6See Note 14. 7See Note 15. 8See Notes 5 and 15. 3A16 Rev. 95 38 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 402. Heater installation (a) Beech 95-550000 cabin heater (modified surface combustion model 83A28) 48 lb. (+ 22) (b) Beech 95-550001-1, -19, -23 45 lb. (+ 19) (c) Beech 95-55000 1-3, -21, -25 35 lb. (+ 22) (d) Beech 95-550002-1, or -195 or -221 45 lb. (+ 18) (e) Beech 95-550002-3, or -197 or -223 40 lb. (+ 20) (f) Beech 95-550002-199 or -219 45 lb. (+ 6) (g) Beech 95-550002-209 or -225 51 lb. (+ 7) (h) Beech 95-550002 Series 45 lb. (- 4) (i) Beech 58-550021 Series 38 lb. (+ 11) 38 lb. (- 1) 38 lb. (- 11) 403. Air conditioner installation (a) Beech 35-050085-1 (including water) 18 lb. (+118) (b) Beech 96-555000 100 lb. (+116) (c) Beech 96-555001 97 lb. (+112) (d) Beech 58-555001 (refrigeration type) 95 lb. (+ 73) Airplane Flight Manual Supplement P/N 58-590000-23 dated April 20, 1977, required (Model 58/58A, S/N TH-680, TH-873, TH-895 and up) X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X (e) Beech 58-555001-3 (refrigeration type) 95 lb. (+ 75) Airplane Flight Manual Supplement P/N 58-590000-23 dated February 5, 1978, or later revision required (Model E55/ E55A, S/N TE-1119, TE-1125 and up) (f) Beech 58-555003 Series (refr. type) 95 lb. (+ 75) Airplane Flight Manual Supplement P/N 58-590000-23 dated October 1983 or later X X X X 404. T-type dual control column (a) Beech 95-524034 3 lb. (+ 72) (b) Beech 95-524045 3 lb. (+ 72) (c) Beech 95-524034-3 and -5 3 lb. (+ 72) (d) Beech 96-524020 3 lb. (+ 72) (e) Beech 95-524034-7 3 lb. (+ 72) 3 lb. (+ 62) (f) Beech 58-524038-1 3 lb. (+ 72) 3 lb. (+ 62) X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 39 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 405. Pilot's Check List (a) 96-590010-3 dated February 11, 1972, or later (S/N TE-768 through TE-879) (b) 96-590008-1 dated April 29, 1974, or later (c) 58-590000-3 dated February 11, 1972, or later (S/N TH-1 through TH-263) (d) 96-590029-1 dated February 11, 1972, or later (S/N TE-768 through TE-879) (e) 58-590014-1 dated February 11, 1972, or later (S/N TH-1 through TH-263) 1 1 X X X X Deicing Equipment (Propeller, Surface and Windshield) 501. Propeller Anti-Icer (a) 1.5 gal. fluid tank, pump and lines for use with propeller Item 1(a)(1) per Beech Dwg. 95-960006 or 95-001027 (Weight includes 11 lb. fluid) 19 lb. (+ 43) (Fluid arm +39) (b) 3.0 gal. fluid tank, pump and lines for use with propeller Item 2(a)(1) or 2(d)(1) or 2(e)(1) or 3(a)(1) per Beech Dwg. 96-960006 Series or 55-001057-1 or Hartzell propellers (STC SA795CE for BHC-C2Y two-blade or PHC-C3Y three-blade propellers) installed per Beech Dwg. 96-960006 Series (Weight includes 22 lb. fluid) 31 lb. (+35) (Fluid arm +33) (c) 3.0 gal. fluid tank, pump and lines for use with propeller Item 1(a)(1) or 4(a)(1) per Beech Dwg. 95-960007 or 55-001057-3. (Weight includes 22 lb. fluid) 31 lb. (+35) (Fluid arm +33) X X X X X X X X X X X X X (d) 3.0 gal. fluid tank, pump and lines for use with propeller Item 2(e)(1) or 5(a)(1) or Hartzell propellers (STC SA773CE for BHC-C2Y two-blade or PHC-C3Y three-blade propellers) installed per Beech Dwg. 96-960008 Series. (Weight includes 22 lb. fluid) 31 lb. (+25) (Fluid arm +21) X X X X X X X X (e) B.F. Goodrich elect ric propeller deicing system, used in conjunction with Hartzell HC-A3 three-bladed propellers (STC SA126CE), installed per Beech Dwg. 96-960009 or 55-4010 14 lb. (+ 31) or used in conjunction with Hartzell PHC-C3Y three-bladed propellers (STC SA795CE) installed per Beech Dwg. 96-960022 14 lb. (+ 31) Airplane Flight Manual Supplement P/N 130478 dated July 26, 1965, or later required. (Excluding 95-B55/ B55A S/N TC-1403 and up.) (f) B.F. Goodrich electric propeller deicing system for use with propeller Item 6(a)(1) per Beech Dwg. 96-960018 9 lb. (+ 18) X X X X X 2 X 2 **See Note 8. ***See Note 9. 1See Note 10. 2See Note 14. 3A16 Rev. 95 40 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Deicing Equipment (Propeller, Surface and Windshield (contd) 501. (g) 3.0 gal. fluid tank, pump and lines for use with propeller Item 7(a)(1) or Hartzell propellers (STC SA773CE) for BHC-J2Y two-blade propellers) installed per Beech Dwg. 96-960008 Series. (Weight includes 22 lb. fluid) 31 lb. (+15) (Fluid arm +11) (h) 3.0 gal. fluid tank, pump and lines for use with propeller Item 8(a)(1) or Hartzell propellers (STC SA773CE) for PHC-J3Y three-blade propellers) installed per Beech Dwg. 96-960008 Series. (Weight includes 22 lb. fluid) 31 lb. (+15)(Fluid arm +11) X X X X (i) 3.0 gal. fluid tank, pump and lines for use with Hartzell propeller Item 12(a)(1) or 12(b)(1) per Beech Dwg. 96-960008 Series. (Weight includes 22 lb. fluid) 31 lb. (+15)(Fluid arm +11) (j) 3.0 gal. fluid tank, pump and lines for use with McCauley propeller Item 13(a) per Beech Dwg. 96-960008 Series. (Weight includes 22 lb. fluid) 31 lb. (+15)(Fluid arm +11) 502. Surface Deicer (a) Wing and tail deicer boots, B.F. Goodrich type installed per Beech Dwg. 95-970000 and B.F. Goodrich STC SA1-395. Weight includes 7 lb. air charged at 3000 psi. Airplane Flight Manual Supplement P/N 95-590014-17 dated April 12, 1960, or revision dated March 10, 1961, required. 60 lb. (+ 77) X X X X X X X X 503. Surface deicer, wing and tail deicer boots B.F. Goodrich type 23 inst alled per B.F. Goodrich STC SA1-395 and Beech Dwg. 95-970000-125 or 95-001037 or per Beech Dwg. 95-970000-129 or 95-001065, or per Beech Dwg. 95-970000-147, or per Beech Dwg. 95- 9700000-185 or 55-001088, or per Beech Dwg. 95- 970000-187 or Mod. C.O. B85503 Weight includes 7 lb. air charged at 3000 psi. Airplane Flight Manua l Supplement P/N 95-590014-47 dated April 12, 1960, revised March 10, 1961, or dated October 1978 or later, required. (a) Reservoir bottle located aft of Sta. 12.00 66 lb. (+ 75) (b) Reservoir bottle located forward Sta. 12.00 66 lb. (+ 68) X X X X 1 2 X X 1S/N TC-191 through TC-399 (except TC-350 and TC-371) 2S/N TC-400 through TC-501 **See Note 8. ***See Note 9. Rev. 95 3A16 41 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 504. Surface deicer, B.F. G oodrich type 23 wing and tail deicer boots and automatic cycling controls. Airplane Flight Manual Supplement P/N 55- 590000-45 dated July 19, 1963; July 16, 1964; December 7, 1964; or later required. (Excluding 95-B55/B55A, S/N TC-1403 and up) (a) Beech Dwg. 96-970001-1 or -79 48 lb. (+110) (b) Beech Dwg. 96-970001-3 47 lb. (+106) (c) Beech Dwg. 55-001087 or 55-4002 48 lb. (+110) (d) Beech Dwg. 55-001087 47 lb. (+106) (e) Beech Dwg. 96-970002 Series or Mod. C.O. B88449 49 lb. (+110) (f) Beech Dwg. 96-970002 Series 47 lb. (+103) 1 1 X X X X X X X X X X X X 3 X X X 3 X X X 2 X X 2 X X (g) Beech Dwg. 96-970004 Series 41 lb. (+137) 40 lb. (+135) 37 lb. (+133) 38 lb. (+134) X X X X X X X X X 505. (a) Goodyear electro-thermal propeller deicer instln. per Beech Dwg. 96-960007 (including Goodyear 4065-2611 or Beech 50-200008-1 ice guard and Goodyear 4065-2420 or Beech 50-300008-3 timer). 11 lb. (+ 30) or B.F. Goodrich electric propeller deicing system used in conjunction with Hartzell BHC-C2Y two-bladed propellers STC SA795CE installed per Beech Dwg. 96-960022 STC SA773CE installed per Beech Dwg. 96-960021 13 lb. (+ 30) Airplane Flight Manual Supplement P/N 55-590000-51 dated July 9, 1964, or later required (Excluding E55, E55A, 95-B55, 95-B55A, S/N TC-1403 and up) X X X X X X X X X X X X (b) B.F. Goodrich electric propeller deicing system used in conjunction with McCauley 3AF32C three-bladed propeller installed per Beech Dwg. 96-960010 or 55-9008 14 lb. (+ 31) or used in conjunction with Hartzell PHC-C3Y three-bladed propellers (STC SA773CE) installed per Beech Dwg. 96-960020 15 lb. (+ 31) Airplane Flight Manual Supplement P/N 130478 dated July 26, 1965, or later required (excluding E55/E55A) X X X X X X X X 1S/N TD-526 through TD-533 **See Note 8. ***See Note 9. 2See Note 10. 3See Note 14. 3A16 Rev. 95 42 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Deicing Equiipment (cont'd) 505. (c) B.F. Goodrich el ectric propeller deicing system for use with propeller Item 7(a)(1) per Beech Dwg. 96-960007 or for use with Hartzell BHC-J2Y two-bladed propellers (STC SA773CE) installed per Beech Dwg. 96-960021 11 lb. (+ 27) (d) B.F. Goodrich electric propeller deicing system for use with propeller Item 8(a)(1) or Hartzell PHC-J3Y three-bladed propellers (STC SA773CE) installed per Beech Dwg. 58-960010 12 lb. (+ 29) (e) B.F. Goodrich elect ric propeller deicing system for use with X X X X (1) Hartzell propeller Item 12(a)(1) installed per Beech Dwg. 96-960021 Series 11 lb. (+ 27) or (2) Hartzell propeller Item 12(b)(1) installed per Beech Dwg. 58-960010 Series 12 lb. (+ 29) (f) McCauley electric propeller deicing system for use with X X X X X X X X X X 506. Surface Deicer (a) B.F. Goodrich type 23 wing and tail deicer boots and automatic cycling controls per Beech Dwg. 96-970002-3 49 lb. (+110) (b) B.F. Goodrich type 23 wing and tail deicer boots and automatic cycling controls per Beech Dwg. 96-970003 Series 44 lb. (+114) (c) B.F. Goodrich type 23 wing and tail deicer boots and automatic cycling controls per Beech Dwg. 96-970005 Series 39 lb. (+138) propeller Item 13(a), installed per Beech Dwg. 58-960019 8 lb. (+ 26) 9 lb. (+ 26) (with air cond.) X X X X 507. Surface deicer, B.F. Goodrich type 25 wing and tail deicer boots and automatic cycling controls (pressure or vacuum pump weight change not included) (a) Beech Dwg. 96-970002 Series 33 lb. (+115) (b) Beech Dwg. 96-970004 Series 26 lb. (+156) 26 lb. (+153) (95-B55 and 95-B55A, S/N TC-2003 and up) (58 and 58A S/N TH-1 through TH-1471) 508. Models E55 and E55A, S/N TE-1084 through TE-1201, are approved for flight into icing conditions when equipped per Beech Kit 55-5019. Airplane Flight Manual Supplement P/N 96- 590010-33 dated September 1984 or later required. X X X X X X X X X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 43 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 509. Models 58 and 58A, S/N TH-1472 through TH-1475, TH-1477 through TH-1486, TH- 1488, TH-1490 and TH-1497, TH-1499 through TH-2124 G58 are approved for flight into icing conditions when equipped per Beech Dwg. X X 510. Models 58 and 58A, S/N TH-1 through TH-1471, TH- 1476, TH-1487, TH-1489 & TH-1498 are approved for flight into icing conditions when equipped per Beech Kit Dwg. 58-5012. Airplane F light Manual Supplement P/N 58-590000-33 dated December 1986 or later required. 3 3 3 3 Miscellaneous (not listed above) 601. Stall warning indicator instln., weight negligible (a) Safe-Flight 35-361025-1 or (b) Safe-Flight No. 168-3 (heated) or No. 190-3 (heated) installed per Dwg. 95-970000 Series or 95-001038 or 58-361013 or (c) Safe-Flight No. 151-3 or No. 151-10 (d) Safe-Flight No. 168-2 or No. 190-3 (heated) or (e) Safe-Flight No. 168-3 (heated) or No. 190-3 (heated) installed per Dwg. 96-970003 Series (f) Safe-Flight No. 151-7 or No. 190-3 (heated) (g) Safe-Flight No. 151-6 (heated) or No. 190-3 (heated) Installed per Beech Dwg. 96-970005 Installed per Beech Dwg. 96-970004 X X X X X X X X X X 1 1 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X 602. Heated pitot head installation 1 lb. (+ 75) 1 lb. (+ 2) 1 lb. (- 8) X X X 2 X 2 X X X X X X X X X X X X X X X X X X X 603. Optional seating arrangements per Beech Dwgs.: (a) 95-534014, 95-534015, 95-534016 15 lb. (+139) (b) 95-534022 (fifth seat) 20 lb. (+153) (c) 95-534022-81 (fifth seat) 20 lb. (+153) X X X X X X (d) 96-534039 or 55-001071, Mod. C.O. B78772 or 55-001071 (fifth and sixth folding seats) 25 lb. (+155) Airplane Flight Manual Supplement P/N 55-590000-33 dated June 14, 1962, or December 18, 1962 (for 400 lb. rear baggage limitation) required (e) 95-534022-83 (fifth seat) 20 lb. (+153) (f) 96-534051 Series or 35-001120 (fifth seat) and Airplane Flight Manual Supplement P/N 55-590000-33 dated December 18, 1962 13 lb. (+155) 3 3 X X X X X X 4 X 4 5 5 5 X 3 3 (g) 96-534051 Series or 35-001120 (fifth and sixth seat instln.) and Airplane Flight Manual Supplement P/N 55-590000-33 dated Dec 18, 1962 26 lb. (+155) (h) 96-534051-73 (fifth folding seat) 13 lb. (+155) (i) 96-534051-75 (fifth and sixth folding seats) 26 lb. (+155) 3 3 X X X X X 5 5 X 3 3 **See Note 8. 3See Note 10 ***See Note 9. 4See Note 13. 1S/N TG-69 through TG-83 5See Note 14. 2S/N TE-938, TE-943 and up 3A16 Rev. 95 44 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Miscellaneous (not listed above) (cont'd) 603. (j) 36-530011 Series (fifth seat) 16 lb. (+155) (k) 36-530011 Series (fifth and sixth) seat instln.) 32 lb. (+155) (l) 58-530061 (club seating) (third and fourth aft facing seats) 40 lb. (+106) (replaces third and fourth forward facing seats) 40 lb. (+117) fifth and sixth forward facing seats 32 lb. (+155) X X X X X X X X X ` X X X X X X X (m) 58-530204 Series or 106-530025 Series (fifth seat instln.) 15 lb. (+155) (n) 58-530204 Series or 106-530025 Series (fifth and sixth seat instln.) 30 lb. (+155) (p) 58-530183 Series or 102-530100 Series (club seating instln.) (third and fourth aft facing seats) 50 lb. (+106) (replaces third and fourth forward facing seats 50 lb. at +122) (fifth and sixth forward facing seats) 30 lb. (+155) X X X X X X X X X X X X X X (q) Vertical adjusting (co-pilot's seat) per Beech Dwg. 106-530060-15 23 lb. (+ 75) (r) 106-530057 Series (fifth seat instln.) 15 lb. (+155) (s) 106-530057 Series (fifth and sixth seat instln.) 30 lb. (+155) X X X X X X X X X X X X X X X X (t) 106-530061 Series (club seating instln.) (third and fourth aft facing seats) 50 lb. (+106) (replaces third and fourth forward facing seats) 50 lb. (+122) (fifth and sixth forward facing seats) 30 lb. (+155) X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 45 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 604. Autopilot instlns. Airplane Flight Manual Supplements required as follows: (a) through (d) (B95, B95A, 95-55); (e) and (f) P/N 130017 dated July 14, 1961, or 65-001021-25 dated March 28, 1962 (95-55, 95-A55, 95-B55); (g), (t) and (u) P/N 95- 590001-5 dated October 6, 1961, or January 7, 1964 (all models except 95-B55B and 56TC); (h) and (m) P/N 130046 dated January 4, 1962 (B95, B95A); (i) through (l) and (r) P/N 130043 dated May 7, 1963, or August 10, 1962 (95-A55); or dated March 22, 1963, or December 24, 1963 or dated December 21, 1963 (95-B55); or P/N 55- 590000-47 dated March 13, 1964 (95-B55, S/N TC-602 and up); or P/N 55-590000-53 dated December 28, 1964 (95-B55, S/N TC-837 and up); (n) P/N 130046 dated December 6, 1961 (95-55); (o), (p) and (q) P/N 65- 001021-25 dated March 28, 1962 (B95, B95A, 95-55, 95-A55); (v) P/N 130388 dated October 25, 1963 (95-55, 95-A55, 95-B55); (w) and (x) 95-590014-67 dated August 19, 1964, or May 25, 1966, or later (D95A, 95-B55, 95-C55); (y) P/N 55-590000- 59 dated July 8, 1965 (95-55, 95-A55, 95-B55); z) and (aa) P/N 95-590014-67 dated May 25, 1966 (D95A, 95-B55, 95-C55); (bb) P/N 55-590000-63 dated September 12, 1966 (95-C55); (cc) P/N 130739 dated October 6, 1967, or later (D55) (a) Tactair T-3 autopilot instln. per Beech Dwg. 95-524041 or Tactair Dwg. A-1565 12 lb. (+132) (b) Altitude hold instln. per Beech Dwg. 95-524041-1 or Tactair Dwg. A-1521 or A-1950 2 lb. (+ 63) (c) Tactair T-3 autopilot instln per Beech Dwg. Mod. C.O. B54453 or Tactair Dwg. A-1875 13 lb. (+145) (d) Altitude hold instln. per Beech Dwg. 96-500001-1 or Tactair Dwg. A-1521 or A-1950 2 lb. (+ 58) (e) Sperry SP-3 with altitude hold per Beech Dwg. 96-500000 or 55-001060-1 36 lb. (+163) X X X X X X X X X X X X X X X X (f) Sperry SP-3 per Beech Dwg. 96-500000-1 or 55-001060-1 31 lb. (+157) (g) Tactair T-3 autopilot instln. per Beech Dwg. 96-500001 or Tactair Dwg. A-2210 13 lb. (+145) (h) Sperry SP-2A per Beech Dwg. 95- 001044-7 25 lb. (+153) (i) Beech H-14 per Beech Dwg. 96-500002-1 or 55-001072 or 55-001075 50 lb. (+173) X X X X X X X X X X X X X X X X **See Note 8. ***See Note 9. 3A16 Rev. 95 46 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Miscellaneous (cont'd) 604. (j) Beech H-14 with altitude controller per Beech Dwg. 96-500002 or 55-001072 or 55-001075 51 lb. (+175) (k) Beech H-14 with altitude and auto-trim per Beech Dwg. 96-500002-3 or 55- 001072 or 55-001075 55 lb. (+176) X X X X X X (l) Beech H-14 with altitude controller, auto- trim and ILS coupler per Beech Dwg. 96-500002-5 or 55-001072 or 55-001075 56 lb. (+175) (m) Sperry SP-2A with altitude hold per Beech Dwg. 95-001044-7 30 lb. (+161) (n) Sperry SP-2A per Beech Dwg. 55-001060-7 25 lb. (+151) (o) Sperry SP-3 pe r Beech Dwg. 95-001044-1 32 lb. (+160) (p) Sperry SP-3 with altitude hold per Beech Dwg. 95-001044-1 37 lb. (+166) (q) Sperry SP-3 course director coupler per Beech Dwg. 55-001070 with Item 604(e) or (f) and ARC CD-1 or CD-3 or CD-4 course director 5 lb. (+212) X X X X X X X X X X X X (r) Beech H-14 with altitude controller, auto-trim and ILS-OMNI coupler per Beech Dwg. 96-500002-13 or 55- 001072 or 55-001075 56 lb. (+175) X X X (s) Beech H-14 heading selector per Beech Dwg. 18-500022 or 55-001072 or 55-001075 for use only with Items 604(i), (j), (k), (l) or (r) 1 lb. (+ 68) (t) Tactair T-3 autopilot instln. per Beech Dwg. 95-500000 or Tactair Dwg. A-2461 13 lb. (+145) (u) Altitude hold instln. per Beech Dwg. 95-500000-1 or Tactair Dwg. A-1521 or A-1950 2 lb. (+ 58) X X X X X (v) Beech H-14 right engine vacuum instln. per Beech Dwg. 55-001084 for use only with Item 604(i), (j), (k), (l) or (r) 5 lb. (+ 50) X X X (w) Tactair T-3AL autopilot instln. per Beech Dwg. 96-500006 or Tactair Dwg. B-2589 15 lb. (+133) X X X X X X (x) Tactair T-3AL autopilot instln. per Beech Dwg. 95- 500001 or Tactair Dwg. B-2588 15 lb. (+133) X **See Note 8. ***See Note 9. Rev. 95 3A16 47 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** Miscellaneous 604. (y) Bendix M4C autopilot instln. per Beech Dwg. Mod C.O. B99377 57 lb. (+159) (z) Tactair T-3ALL autopilot instln. per Beech Dwg. 96- 500007 or Tactair Dwg. A-3110 15 lb. (+133) X X X X X X X X X X (aa) Tactair T-3ALL autopilot instln. per Beech Dwg. 95-500002 or Tactair Dwg. A-3108 15 lb. (+133) (bb) Beech H-14 with altitude controller auto-trim, ILS-OMNI coupler and electric heading selector per Beech Dwg. Mod. C.O. C12597 or 96-500009 53 lb. (+169) (cc) Beech H-14 with altitude controller auto-trim, S-OMNI coupler and electric heading selector per Beech Dwg. 96-500008 60 lb. (+183) (dd) Beech H-14 with altitude controller, auto-trim, ILS-OMNI coupler and electric heading per Beech Dwg. 96- 500038 56 lb. (+180) (ee) Beech H-14 with altitude controller, auto-trim, ILS-OMNI coupler and electric heading selector per Beech Dwg. 96-500009- 69 through -79 Series 57 lb. (+177) X X X X X X X X X X X 605. Emergency static source instln. (a) Beech Dwg. 95-001039 or Beech Dwg. 96-324068 (Basic) Airplane Flight Manual Supplement P/N 95-590014-45 dated March 10, 1961, required (S/N TD-534 through TD-619) or dated March 17, 1965, required (S/N TD-620 through TD-707) Airplane Flight Manual Supplement P/N 55-590000-21 dated November 9, 1960, required (S/N TC-371, TC-502 through TC-875) or dated March 17, 1965, required (S/N TC-876, TC-878, TC-880, TC-881, TC-898 through TC-954) Weight negligible (b) Beech Dwg. 58-5006 Item 401(ac) or (ad) required (S/N TC-371, TC-502 through TC-954) Item 401(ae) required (S/N TC-955 through TC-1156) Item 401(af) required (S/N TC-1157 through TC-1372) Item 401(ag) required (S/N TC-502 through TC-1372) Item 401(pp) required (S/N TE-768 through TE-832) Item 401(rr) required (S/N TH-1 through TH-106) Weight negligible X X X X X X X X 1 1 2 2 X X X X X **See Note 8. ***See Note 9. 1See Note 13. 2See Note 14. 3A16 Rev. 95 48 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 606. Oxygen installation (a) Scott high pressure per Beech Dwg. Mod. C.O. B49061 or Mod. C.O. B59639 38 lb. (+ 30) (b) Zep high pressure per Beech Dwg. 96-560001 (38 cu. ft. aft bottle instln.) 29 lb. (+172) X X X X X X X (c) Zep high pressure per Beech Dwg. 96-560001-1 (48 cu. ft. aft bottle instln.) 35 lb. (+173) (d) Zep high pressure per Beech Dwg. 95-560000 (38 cu. ft. nose bottle instln.) 31 lb. (+ 21) (e) Scott high pressure per Beech Dwg. Mod. C.O. B59638 32 lb. (+ 20) X X X X X X X (f) Zep oxygen system per Beech Dwg. 95-001042-1 or -3 or -5 and Beech Dwg. 414-001058-1 or 414-001059-1 Use actual weight change (g) Zep high pressure per Beech Dwg. Mod. C.O. B85111A or 96-560002 (48 cu. ft. fwd. bottle instln.) 35 lb. (+ 52) (h) Zep high pressure per Beech Dwg. Mod. C.O. B85111A or 96-560002 (38 cu. ft. fwd. bottle instln.) 30 lb. (+ 54) X X X X X X X X X (i) Zep high pressure per Beech Dwg. 96-560001 (38 cu. ft. aft bottle instln.) 29 lb. (+163) (j) Zep high pressure per Beech Dwg. 96-560001 (48 cu. ft. aft bottle instln.) 35 lb. (+165) (k) Scott high pressure per Beech Dwg. 96-560003 (aft bottle instln.) 29 lb. (+160) (l) Scott high pressure per Beech Dwg. 96-560004 (38 cu. ft. fwd. bottle instln.) 30 lb. (+ 50) X X X X X X X X X X X X (m) Scott high pressure per Beech Dwg. 96-560004 (48 cu. ft. fwd. bottle instln.) 36 lb. (+ 49) (n) Scott high pressure per Beech Dwg. 96-560013 and 35-560001 (38 or 49 cu. ft. fwd. bottle instln.) 30 lb. (+ 50) (o) Scott high pressure per Beech Dwg. 96-560014 and 35-560001 (38 cu. ft. fwd. bottle instln.) 32 lb. (+178) X X X X X X X X X X X X X X X X X X X X X (p) Scott high pressure per Beech Dwg. 96-560014 and 35-560001 (49 cu. ft. fwd. bottle instln.) 32 lb. (+177) (q) Scott high pressure per Beech Dwg. 96-560013 and 35-560001 (66 cu. ft. fwd. bottle instln.) 36 lb. (+ 49) X X X X X X X X X X X X X X X X X X (r) Scott high pressure per Beech Dwg. 96-560013 and 35-560001 (114 cu. ft. fwd. bottle instln.) 53 lb. (+ 47) X X X X X X X X X **See Note 8. ***See Note 9. Rev. 95 3A16 49 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 606. Oxzygen installation (cont'd) (s) High pressure per Beech Dwg. 58-560000 and 58-560011 (49 cu. ft. fwd. bottle instln.) 33 lb. (+ 56) 33 lb. (+ 46) (t) High pressure per Beech Dwg. 58-560000 and 58-560011 (65 cu. ft. fwd. bottle instln.) 39 lb. (+ 54) 39 lb. (+ 44) (u) High pressure per Beech Dwg. 58-560000 and 58-560011 (114 cu. ft. fwd. bottle instln.) 57 lb. (+ 50) X X X X X X X X X (v) High pressure per Beech Dwg. 58-560001 49 cu. ft. fwd. bottle instln. 34 lb. (+ 50) 35 lb. (+ 50) 35 lb. (+ 42) or 66 cu. ft. fwd. bottle instln. 40 lb. (+ 48) 41 lb. (+ 48) 41 lb. (+ 40) X X X X X X X X X X X X (w) High pressure per Beech Dwg. 58-560003 49 cu. ft. fwd. bottle instln. 34 lb. (+ 50) 35 lb. (+ 50) 35 lb. (+ 42) or 66 cu. ft. fwd. bottle instln. 40 lb. (+ 48) 41 lb. (+ 48) 41 lb. (+ 40) X X X X X X X X X X X X X X X X 607. Aft baggage compartment instln. per Beech Dwg. Mod. C.O. B82155 or 96-400000-3. Combined weight of luggage and/or equipment must not exceed 120 lb. Loading placard P/N 96- 534050 required. 12 lb. (+181) X X X X 608. Landing gear safety system instln. per Beech Dwg. 96-810022. Airplane Flight Manual Supplement P/N 130538 dated May 27, 1966, or later required. (Exc luding E55, E55A, 56TC, A56TC, 58, 58A, and 95-B55, 95-B55A, S/N TC-1403 and up) 3 lb. (+100) X X X X X X X X X X X X X X X 609. Elevator electrical trim control instln. per Beech Dwg. 96-524031 Series or Beech Dwg. 55-3014 3 lb. (+205) X X X X X X X X X X X X X X 610. Area Navigation Equipment installed per applicable Beech Dwgs. Airplane Flight Manual Supplement P/N 96-590011-5 dated September 3, 1971, or September 8, 1972, or later required. Airplane Flight Manual P/N 58-590000-7 dated August 23, 1971, or Airplane Flight Manual Supplement P/N 96-590011-5 dated September 8, 1972, or later required. Airplane Flight Manual Supplement P/N5A 96-590010-19 dated October 1976 or later required (95-B55 and 95-B55A S/N TC-2003 and up)(E55 and E55A S/N TE-1084 and up) (58 and 58A S/N TH-773 and up) 1 1 1 1 1 1 1 1 1 1 X X X **See Note 8. ***See Note 9. 1See Note 11. 3A16 Rev. 95 50 D55 D55A E55 E55A 56TC A56TC 58*** 95 B95 B95A D95A E95 95-55 95-A55 95-B55 95-B55A 95-B55B 95-C55 95-C55A 58A*** 58** 58A** 611. Models 58 and 58A are a pproved for flight with both utility doors removed when provisions for utility door removal are made per Beech Drawing 58-430010. X X X X 612. Area navigation equipment installed per applicable Beech dwgs. (a) Bendix NCP2040 Nav Programmer System (RNAV) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement P/N 96-590011-21 dated June 2, 1977, or later required. (b) Air Data AD611/D RNAV System Pilot's Operating Handbook and FAA Approved Airpla ne Flight Manual Supplement P/N 58-590000-25 dated June 21, 1977, or later required. (c) Collins ANS-351 Area Navigation System (RNAV) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement P/N 106-590000-15 dated November 16, 1977, or later required. (d) King KNS-80 Area Navigation System Pilot's Operating Handbook and FAA Approved Airpla ne Flight Manual Supplement, P/N 58-590000-29 dated January 1979, or later revision (e) Narco RNAV 161 Area Navigation Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement, P/N 96-590010-27 dated January 1979, or later required. (f) King KNC-610 Area Navigation System Pilot's Operating Handbook and FAA Approved Airpla ne Flight Manual Supplement, P/N 102-590000-45 dated November 1978, or later required. (g) Air Data AD-511 Area Navigation System Pilot's Operating Handbook and FAA Approved Airpla ne Flight Manual Supplement, P/N 58-590000-27 dated December 1978, or later required. (h) King KNS-81 Area Navigation System Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement, P/N 102-590000-53 dated January 1980 or later. 613. Loran Navigation Equipment installed per applicable Beech drawings. (a) Bendix/King KLN88 Loran Navigation System Pilot's Operating Handbook and FAA Approved Airplane Fli ght Manual Supplement, P/N 58-590000-51 dated March 1990 or later. X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X **See Note 8. ***See Note 9. Rev. 92 3A16 51 NOTE 1. Current weight and balance report including list of e quipment included in certificated empty weight, and loading instructions when necessary must be provided for ea ch aircraft at the time of original certification. The certificated empty weight and co rresponding center of gravity locations must include system (undrainable) oil (not included in oil capacity) and unusable fuel (not included in usable fuel) as follows: Unusable Fuel Weight (lb.) Arm (a) Models 95 and B95 Standard fuel system or optional Item 106 41 +79 (b) Models 95-55, 95-A55, 95-B55, 95-B55A, (S/N TC-1 through TC- 1607 except TC-350, TC-1393 through TC-1396, and TC-1402) 95-C55, 95-C55A, D55, D55A E55 and E55A. (S/N TC-350, TE-1 through TE-942 except TE-50 and TE-938) Standard fuel system or optional Item 108 41 +79 (c) Models 95-B55 and 9-B55A (S/N TC-1608 and on) Standard fuel system or optional Item 116 36 +79 (d) Models E55 and E55A (S/N TE-938, TE-943 and on) Standard fuel system or optional items 114 and 116 36 +79 (e) Models B95A, D95A, and E95 Standard fuel system or optional Item 109 36 41 +79 +79 (f) Model 95-B55B Standard fuel system 41 +79 (g) Models 58 and 58A Standard fuel system or optional Item 114 or optional Item 117 36 +79 (h) Models 56TC and A56TC Item 113 (1) 25 +79 with unbaffled (2) 114 +76 Inboard leading edge tanks in either or both wings Item 113 (1) 25 +79 with baffled (2) 36 +78 Inboard leading edge tanks (1) Prior to compliance with S.I. 0559-281, Rev. 1. (2) After compliance with S.I. 0559-281, Rev. 1 (j) Model 95-B55 (S/N TC-1475 through TC-1480, TC-1575 TC-1579, TC-1584, TC-1587 and TC-1593) Optional Item 118 36 +79 (k) Model G58 Standard fuel system 36 +79 Unusable Oil Weight (lb.) Arm All models except 56TC and A56TC 56TC and A56TC 9 0 +42 NOTE 2. The following placards and/or marki ngs must be displayed in locations indicated: (a) L.H. side adjacent to pilot (exc luding Models 95-B55B, 56TC and A56TC): "This airplane must be operated as a normal category ai rplane in compliance with the Airplane Flight Manual. No acrobatic maneuvers including spins approved." (b) On inside rear baggage compartment door: "Baggage compartment. Load in accordance with Airplane Flight Manual. Maximum structural capacity 400 pounds." or when extended baggage compartment is installed: "Baggage compartments: Load in accordance with Airplane Flight Manual (or weight and balance data). Maximum structural capacity - Main compartment 400 pounds – Aft compartment 120 pounds." 3A16 Rev. 921 52 NOTE 2. (cont'd) (c) In plain view when nose baggage compartment is open: "Baggage compartment. Load in accordance with Airplane Flight Manual (or weight and balance data). Maximum structural capacity - 270 lb (or 300 lb. - See NOTE 3)." (d) Adjacent to cabin door handle: "Rotate to full locked position." (e) On left cabin sidewall below window sill and close to emergency exit release handle when more than five seats are installed: "Emergency exit - Pull pin - Push window out." (f) L.H. side below ignition switch panel (Model 95-B55B only): "Normal and Utility Category. This airplane must be operated as a Normal or Utility Category airplane in compliance with the operating limitations stated in the form of placards, markings and manuals. No acrobatic maneuvers approved except thos e in the Airplane Flight Manual." (g) L.H. cabin side adjacent to ignition switch panel (Model 56TC and A56TC only): "This airplane must be operated as a Normal Cate gory airplane in compliance with the operating limitations stated in the form of placards, markings and manuals (Pilot's Check List). Occupied seats must be in upright position during takeoff and landing. Maximum weight 5990 lb. No acrobatic maneuvers including spins approved. Maximum speed w/landing gear extended (normal) (TG-1 through TG-71) 165 m.p.h. (143 knots) (TG-72 and up) 175 m.p.h. (152 knots) Max. speed with flaps extended (15° down) 175 m.p.h. (152 knots) Max. speed with flaps extended (normal) 144 m.p.h. (125 knots) Max. design maneuver speed 183 m.p.h. (159 knots) Minimum control speed single engine 97 m.p.h. ( 84 knots) Max. structural cruising speed (S.L. to 20,000 ft. alt.) 233 m.p.h. (202 knots) Max. structural cruising speed (25,000 ft. alt.) 222 m.p.h. (193 knots) Max. structural cruising speed (30,000 ft. alt.) 214 m.p.h. (186 knots) Never exceed speed (S.L. to 20,000 ft. alt.) 262 m.p.h. (227 knots) Never exceed speed (25,000 ft. alt.) 249 m.p.h. (216 knots) Never exceed speed (30,000 ft. alt.) 240 m.p.h. (208 knots) (h) Floating instrument panel near airspeed indicator (Model 56TC, A56TC): "See limitations placard for 'max structural cruise' and 'never exceed' limits" (i) On lower side well adjacent to pilot: "Warning - Emergency airspeed static source - see Airplane Flight Manual (Pilot's Check List) emergency procedures for airspeed and altimete r calibration - on-emergency off-normal." (j) On pilot's storm window: (Excluding Models E55, E55A, A56TC, 58, G58, 58A, 95-B55 (S/N TC-1403 and on) and 95-B55A (S/N TC-1403 and on)) "Caution - Do not open above 145 m.p.h. (126 knots)." (k) Between front seats on spar cover: "Emergency landing gear - Instructions to extend - Engage handle in rear of front seat and turn counter clockwise as far as possible (50 turns)." (l) On middle windows: "Latch windows before takeoff." "Do not open in flight." (m) On oxygen console: "Warning - Do not smoke while oxygen is in use. Hose plug must be pulled out to stop flow of oxygen." Rev. 92 3A16 53 NOTE 2. (cont'd) (n) L.H. cabin side adjacent to ignition switch panel (Model E55 S/N TE-768 through TE-879): "This airplane must be operated as a Normal Category ai rplane in compliance with the operating limitations stated in the form of placards, markings and manual. (Pilot's Check List). Occupied seats must be in upright position during takeoff and landing. Maximum weight 5300 lb. No acrobatic maneuvers including spins approved. Max. speed w/landing gear extended (normal) 175 m.p.h. (152 knots) Max. speed with flaps extended (15° down) 175 m.p.h. (152 knots) Max. speed with flaps extended (normal) 140 m.p.h. (122 knots) Max. design maneuver speed 180 m.p.h. (156 knots) Minimum control speed single engine 93 m.p.h. ( 81 knots) Max. structural cruisi ng speed 225 m.p.h. (195 knots) Never exceed speed 257 m.p.h. (223 knots) (o) L.H. cabin side adjacent to ignition sw itch panel (Model 58 S/N TH-1 through TH-263): "This airplane must be operated as a Normal Category airp lane in compliance with the operating limitations stated in the form of placards, markings and manual. (Pilot's Check List). Occupied seats must be in upright position during takeoff and landing. Maximum weight 5400 lb. No acrobatic maneuvers including spins approved. Max. speed w/landing gear extended (normal) 175 m.p.h. (152 knots) Max. speed with flaps extended (15° down) 175 m.p.h. (152 knots) Max. speed with flaps extended (normal) 140 m.p.h. (122 knots) Max. design maneuver speed 180 m.p.h. (156 knots) Minimum control speed single engine 93 m.p.h. ( 81 knots) Max. structural cruisi ng speed 225 m.p.h. (195 knots) Never exceed speed 257 m.p.h. (223 knots) (p) L.H. cabin side adjacent to ignition switch panel (S/N TE-768 through TE-879 (E55A); S/N TH-1 through TH-263 (58A)): "This airplane must be operated as a Normal Category ai rplane in compliance with the operating limitations stated in the form of placards, markings and manual. (Pilot's Check List). Occupied seats must be in upright position during takeoff and landing. Maximum weight 4990 lb. No acrobatic maneuvers including spins approved. Max. speed w/landing gear extended (normal) 175 m.p.h. (152 knots) Max. speed with flaps extended (15° down) 175 m.p.h. (152 knots) Max. speed with flaps extended (normal) 140 m.p.h. (122 knots) Max. design maneuver speed 180 m.p.h. (156 knots) Minimum control speed single engine 93 m.p.h. ( 81 knots) Max. structural cruisi ng speed 225 m.p.h. (195 knots) Never exceed speed 257 m.p.h. (223 knots) (q) Instrument Markings: Models E55 and E55A (S/N TE-768 through TE-879) Airspeed Red Radial 257 m.p.h. (223 knots) Yellow Arc 225 - 257 m.p.h. (195 - 223 knots) Green Arc 88 - 225 m.p.h. (76 - 195 knots) White Arc 77 - 140 m.p.h. (67 - 122 knots) Blue Radial 115 m.p.h. (100 knots) Oil Temp. Yellow Radial 75° F. Green Arc 75° - 240° F. Red Radial 240° F. Oil Pressure Red Radial 30 p.s.i. Green Arc 30 - 60 p.s.i. Red Radial 100 p.s.i. Fuel Quantity Yellow Arc E. to 1/2 Standard Fuel Yellow Arc E. to 1/4 Optional Fuel Cylinder Head Temp. Green Arc 200° - 460° F. Red Radial 460° F. 3A16 Rev. 921 54 NOTE 2. (cont'd) (q) Instrument Markings: (cont'd) Models E55 and E55A (S/N TE-768 through TE-879) (cont'd) Fuel Flow and Pressure Red Radial 1.5 p.s.i. Green Arc (Cruise) 9.7 - 170 g.p.h. Green Arc (Takeoff and Climb) 17.8 - 24.3 g.p.h. Red Radial 17.5 p.s.i. Tachometer Green Arc 2000 - 2700 r.p.m. Red Radial 2700 r.p.m. Manifold Pressure Green Arc 15 - 29.6 in. hg. Red Radial 29.6 in. hg. Pressure Gauge Yellow Arc 2.5 - 3.5 in. hg. Green Arc 3.5 - 5.5 in. hg. Yellow Arc 5.5 - 6.5 in. hg. or (red buttons source failure indicators) Pressure Gauge Green Arc 4.3 - 5.9 in. hg. or (red buttons source failure indicators) Deice Pressure Automatic System Red Radial 9 p.s.i. Green Arc 9 - 20 p.s.i. Red Radial 20 p.s.i. Airspeed Red Radial 262 m.p.h. (227 knots) Yellow Arc 233 - 262 m.p.h. (202 - 227 knots) Green Arc 99 - 233 m.p.h. (86 - 202 knots) White Arc 84 - 144 m.p.h. (73 - 125 knots) Blue Radial 121 m.p.h. (105 knots) Oil Temp. Green Arc 38° - 118° C. Red Radial 118° C. Red Radial 38° C. Oil Pressure Green Arc 60 - 90 p.s.i. Red Radial 25 and 100 p.s.i. Cylinder Head Temp. Green Arc 121° - 232° C. Red Radial 246° C. Fuel Flow Green Arc 12 - 50 g.p.h. 55 percent 15.5 - 18 g.p.h. 65 percent 18 - 21 g.p.h. 75 percent 21 - 24 g.p.h. Takeoff S.L. 42 - 47 g.p.h. Takeoff 10K 39.5 - 44 g.p.h. Tachometer Green Arc 2350 - 2900 r.p.m. Red Radial 2900 r.p.m. Manifold Pressure Green Arc 14 - 41.5 in. hg. Red Radial 41.5 in. hg. Turbine Inlet Temp. Red Radial 1650° F. Pressure Gauge Green Arc 3.5 in. hg. - 5.5 in. hg. Yellow Arc 5.5 in. hg. - 6.5 in. hg. Yellow Arc 2.5 in. hg. - 3.5 in. hg. or (red buttons source failure indicators) Pressure Gauge Green Arc 4.3 in. hg. - 5.9 in. hg. (red buttons source failure indicators) Deice Pressure Red Radial 9 p.s.i. Green Arc 9 - 20 p.s.i. Red Radial 20 p.s.i. Propeller Anti-Ice Green Arc 14 - 18 amps. Rev. 92 3A16 55 NOTE 2. (cont'd) (q) Instrument Markings: (cont'd) Models 58 and 58A (S/N TH-1 through TH-263) Airspeed Red Radial 257 m.p.h. (223 knots) Yellow Arc 225 - 257 m.p.h. (195 - 223 knots) Green Arc 95 - 225 m.p.h. (82 - 195 knots) White Arc 83 - 140 m.p.h. (72 - 122 knots) Blue Radial 115 m.p.h. (100 knots) Oil Temp. Yellow Radial 75° F. Green Arc 75° - 240° F. Red Radial 240° F. Oil Pressure Red Radial 30 p.s.i. Green Arc 30 - 60 p.s.i. Red Radial 100 p.s.i. Cylinder Head Temp. Green Arc 200° - 460° F. Red Radial 460° F. Fuel Flow and Red Radial 1.5 p.s.i. Green Arc (Cruise) 9.7 - 17.0 g.p.h. Pressure Green Arc (Takeoff and Climb) 17.8 - 24.3 g.p.h. Red Radial 17.5 p.s.i. Tachometer Green Arc 2000 - 2700 r.p.m. Red Radial 2700 r.p.m. Manifold Pressure Green Arc 15 - 29.6 in. hg. Red Radial 29.6 in. hg. Pressure Gauge Yellow Arc 2.5 - 3.5 in. hg. Green Arc 3.5 - 5.5 in. hg. Yellow Arc 5.5 - 6.5 in. hg. (red buttons source failure indicators) Pressure Gauge Green Arc 4.3 - 5.9 in. hg. or (red buttons source failure indicators) Deice Pressure Automatic System Red Radial 9 p.s.i. Green Arc 9 - 20 p.s.i. Red Radial 20 p.s.i. Fuel Quantity Yellow Arc E. to 1/8 (r) On pilot's shock mounted instrument panel or imme diately forward of the fuel selector handles for the following models with 25 gal. or 40 gal. main fuel tanks installed: 95, B95, B95A, D95A, E95, 95-55, 95- A55, 95-C55, 95-C55A, D55, D55A, 95-B55 (25 gal. tank - S/N TC-371, TC-502 th rough TC-1382). 95-B55A (25 gal. tanks - S/N TC-502 through TC-1382), 95-B55 (40 gal. tanks - S/N TC-371, TC-502 through TC-1298), 95-B55A (40 gal. tanks) - S/N TC-502 through TC-1298), 95-B55B (40 gal. tanks - S/N TF-1 through TF-65). "Takeoff and land on main tanks only. Turning type takeoffs or takeoffs immediately following a fast taxi turn prohibited. Refer to FAA F light Manual for other Fuel System Limitations." Note: This placard not required when both L.H. and R.H. main fuel tanks are installed in the above aircraft per Item 115. (s) Between Fuel Selector Handles: "Use auxiliary tanks and crossfeed in level flight only" (Excluding Models 56TC, A56TC, 58, G58 and 58A) "Use crossfeed in level flight only" (Models 95-B55 and 95-B55A S/N TC-1608 and up) (Models E55 and E55A S/N TE-938, TE-943 and up) (Models 58, G58 and 58A) (t) On pilot's shock mounted instrument panel or on fuel selector panel or fuel selector cover in full view of pilot: “Do not take off if fuel quantity gages indicate in ye llow arc or with less than 13 gallon in each main tank." (u) Model G58 (S/N TH-2173 and on) In full view of the pilot: “NO SMOKING” 3A16 Rev. 921 56 NOTE 3. Airplane S/N's TC-955 and up are eligible for a max imum weight of 5100 lb. extended forward C.G. range, flap extension speed of 140 m.p.h. (122 knots) and forwar d baggage compartment loading of 300 lb. S/N's TC-371, TC-502 through TC-954 are eligible for 5100 lb. gross we ight when modified in accordance with Beech Aircraft Kit Dwg. 55-4014. NOTE 4. The following information shall be provided in the fo rm of placards, markings or manuals (Pilot's Check List) (Models 56TC and A56TC only): (a) Maximum altitude loss during stall recovery is 450 ft. (b) Maximum flight maneuver load factor: flaps up 3.8G, flaps down 2.0G. (c) Weight and balance data. NOTE 5. Airplane S/N TC-502 and on (Model 95-B55), TE-1 through TE-451 (Model 95-C55), TE-452 through TE-767 (Model D55) and TE-768 and on (Model E55) are eligible for a maximum gross weight of 4990 lb. and model designation of 95-B55A, 95-C55A, D55A and E55A, respectively, when modified in accordance with Beech Aircraft Dwg. 96-590028. Airplane S/N TH-1 through TH-2124 (Model 58) are eligible for a maximum gross weight of 4990 lb. and model designation of 58A when modified in accordance with Beech Aircraft Dwg. 58-590013. NOTE 6. One 60 amp alternator listed in 301(q) can be used as a spares replacement for one 50 amp alternator listed in 301(m) per Beech Kit 55-3020. NOTE 7. Airplane S/N TC-2285 and on (Model 95-B55), Airplane S/N TE-1171 and on (Model E55), and Airplane S/N TH-1090 through S/N TH-1395 except S/N TH-1389 (Model 58) are not e ligible for McCauley Propellers pending demonstration of compliance with the noise requirements in accordance with Part 36 of the Federal Aviation Regulations. NOTE 8. Model 58/58A Serial Nos. elig ible TH-1389, TH-1396 through TH-2124. NOTE 9. Model 58/58A Serial Nos. eligib le TH-1 through TH-1395, except TH-1389. NOTE 10. Pilot's Operating Handbook (POH) and Airplane Fli ght Manual (AFM) P/N 96-590010-29 dated July 1979 or later may replace, and be used in lieu of, Airplane F light Manual Supplements (AFMS) P/N 130486, P/N 130793, P/N 55-590000-45, P/N 95-001035, P/N 130776, P/N 96-590011-7 and P/N 55-590000-33; AFM P/N 130738, P/N 130820, P/N 130837, P/N 130836, P/N 96-590010-5 and P/N 55-590006-3; Pilot's Check Lists P/N 96-590010-3 and P/N 96-590029-1. NOTE 11. AFMS P/N 96-590010-19, -21 and -23 may replace and be used in lieu of AFMS 96-590011-5, 131176 and 131271 respectively. NOTE 12. POH and AFM P/N 96-590010-31 dated March 1979 or late r may replace and be used in lieu of AFM P/N 96-590010-9. NOTE 13. POH and AFM P/N 55-590000-65 dated November 1978 or later may replace and be used in lieu of AFMS P/N 96-590011-7, P/N 55-590000-21, P/N 55-590000- 37, P/N 55-001069, P/N 130776, P/N 55-590000-33; AFM P/N 55-590000-3 and P/N 590000-27. NOTE 14. POH and AFM P/N 96-590011-25 dated October 1978 or la ter may replace and be used in lieu of AFM P/N 55-590000-43, P/N 130835, P/N 130544, P/N 55-590000-55, P/N 130821, an d 96-590011-1; AFMS P/N 96-590011-7, P/N 55-590000-45, P/N 130478, P/N 55-590000-21, P/N 55- 001069, P/N 130776 and P/N 55-590000-33. NOTE 15. POH and AFM P/N 96-590011-23 dated May 1978 or late r may replace and be used in lieu of AFM P/N 96-590011-11. NOTE 16. AFMS P/N 58-590000-33 is for use with POH and AFM P/N 55-590000-21, P/N 58-590000-31 & P/N 58-590000-35 only, not with AFM 58-590000-11 or 58-590000-15. NOTE 17. Company name change effective 4/15/96. The followi ng serial numbers are manufactured under the name of Raytheon Aircraft Company: 58, G58: TH-1780 through TH-2177 (RAC). NOTE 18. Company name change effective 3/26/2007. The followi ng serial numbers are manufactured under the name of Hawker Beechcraft Corporation: G58: TH-2178 through TH-2368 (HBC) Rev. 92 3A16 57 NOTE 19. Company name change effective 4/12/2013. The following se rial numbers are manufactured under the name of Beechcraft Corporation: G58: TH-2369 through TH-2442. NOTE 20. Company name change effective 10/12/16. The following serial numbers are manufactured under the name of Textron Aviation Inc.: G58: TH-2470 and On. Contact Beechcraft Corporation as necessary to obtain availability information concerning the drawings and kits which are referenced by this publication. In addition to the placards specified above, the operating limitations indicated by an asterisk (*) under Sections I through X of this aircraft specification must also be displayed by permanent markings. Fuel filler opening may be marked in accordance with FAR 23.1557(c) with word "fuel," and minimum grade, or CAR 3.767(a) with word "fuel," minimum octane rating and usable quantity. ..... END ..... ``` ## ADs (77, first 50, in force first) - [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2014-26-05](https://openairdocs.org/ad/2014-26-05): Fuel · Textron G58. Effective Feb 9, 2015 - [AD 2013-16-01](https://openairdocs.org/ad/2013-16-01): Elevator Balance Weight · Textron 56TC, 58, 95-C55 and 3 more. Effective Sep 24, 2013 - [AD 2012-21-05](https://openairdocs.org/ad/2012-21-05): Electrical power · Textron G58. Effective Nov 27, 2012 - [AD 2012-10-02](https://openairdocs.org/ad/2012-10-02): Fuel · Textron 58 and G58. Effective Jun 21, 2012 - [AD 2011-27-04](https://openairdocs.org/ad/2011-27-04): Airspeed Indicator · Two Teledyne Continental Motors model IO-550-C engines… (Mike Jones Aircraft Sales STC SA1762SO). Effective Dec 29, 2011 - [AD 2010-06-02](https://openairdocs.org/ad/2010-06-02): Landing Gear · Textron G58. Effective Apr 15, 2010 - [AD 2009-25-01](https://openairdocs.org/ad/2009-25-01): Shoulder harnessess · Textron 58, 58A, 58P and 12 more. Effective Jan 8, 2010 - [AD 2008-13-17](https://openairdocs.org/ad/2008-13-17): Circuit breaker toggle switches · Textron 58, 58P, 58TC and 14 more. Effective Aug 6, 2008 - [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008 - [AD 2008-02-06](https://openairdocs.org/ad/2008-02-06): GSM 85 servo gearbox units · Cessna 182T, 206H, LC40-550FG and 11 more. Effective Feb 26, 2008 - [AD 2007-08-08](https://openairdocs.org/ad/2007-08-08): Uplock roller · Textron 35, 35-33, 35-A33 and 49 more. Effective May 25, 2007 - [AD 2007-06-07](https://openairdocs.org/ad/2007-06-07): Left propeller accumulator oil tube assembly · Textron 58 and G58. Effective Apr 19, 2007 - [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2004-25-16 R1](https://openairdocs.org/ad/2004-25-16-R1): Fuel regulator shutoff valve · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 64 more. Effective Jun 20, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2004-21-05](https://openairdocs.org/ad/2004-21-05): B-Seires Combustion Heaters · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 41 more. Effective Nov 19, 2004 - [AD 2003-01-01](https://openairdocs.org/ad/2003-01-01): Right hand fuselage panel assembly · Textron 36, 58, 58A and 3 more. Effective Feb 27, 2003 - [AD 2002-11-07](https://openairdocs.org/ad/2002-11-07): Electroluminescent panel retaining screw. · Textron 58, 58A, 58P and 6 more. Effective Jul 15, 2002 - [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001 - [AD 2001-23-10](https://openairdocs.org/ad/2001-23-10): Flap Flex Shaft Assemblies · Textron 35, 35-33, 35-A33 and 60 more. Effective Dec 13, 2001 - [AD 2001-11-03](https://openairdocs.org/ad/2001-11-03): Blower Motor Circuit · Textron 1900D, 58, 58A and 5 more. Effective Jul 20, 2001 - [AD 2001-10-09](https://openairdocs.org/ad/2001-10-09): Automatic Flight Control Systems · Aerostar PA-60-700P (Aerostar 700P), 208, 208B and 15 more. Effective Jun 15, 2001 - [AD 2000-24-04](https://openairdocs.org/ad/2000-24-04): Rudder Control Cables · Textron 58, A36 and B36TC. Effective Jan 5, 2001 - [AD 2000-22-18](https://openairdocs.org/ad/2000-22-18): Rudder Bellcrank Interconnect Tube · Textron 58. Effective Dec 29, 2000 - [AD 2000-18-02](https://openairdocs.org/ad/2000-18-02): Elevator Skin Assemblies · Textron 56TC, 58, 58P and 12 more. Effective Sep 22, 2000 - [AD 99-05-13 R1 WD](https://openairdocs.org/ad/99-05-13-R1-WD): Withdrawal of AD 99-05-13 · Beech B17B, B17L, B17R (Army UC-43H) and 107 more. Effective Jul 5, 2000 - [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000 - [AD 99-09-15](https://openairdocs.org/ad/99-09-15): Flight Control Mechanism · Textron 1900D, 58, 58A and 5 more. Effective May 18, 1999 - [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998 - [AD 98-04-24](https://openairdocs.org/ad/98-04-24): AFM - Limitations Section - Icing · Textron 100, 300, 58 and 13 more. Effective Mar 13, 1998 - [AD 97-16-10](https://openairdocs.org/ad/97-16-10): Filters · Cessna 310R, T310R, 36 and 17 more. Effective Sep 18, 1997 - [AD 97-14-15](https://openairdocs.org/ad/97-14-15): Cabin Side Door And Utility Door Handle · Textron 36, 50, 56TC and 41 more. Effective Sep 2, 1997 - [AD 95-26-15 R1](https://openairdocs.org/ad/95-26-15-R1): Traffic Alert and Collision Avoidance Systems · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 159 more. Effective Dec 26, 1996 - [AD 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996 - [AD 93-01-23](https://openairdocs.org/ad/93-01-23): Crossfeed Check Valves · Textron 58 and 58A. Effective Mar 12, 1993 - [AD 93-03-02](https://openairdocs.org/ad/93-03-02): Loran Receiver System · Textron 58, A36, B36TC and 1 more. Effective Mar 12, 1993 - [AD 92-23-04](https://openairdocs.org/ad/92-23-04): Engine Control Support Structure · Textron 58, 58A, 58P and 3 more. Effective Dec 8, 1992 - [AD 91-17-01](https://openairdocs.org/ad/91-17-01): Elevator Trim Tab Actuators · Textron 35-33, 35-A33, 35-B33 and 40 more. Effective Nov 25, 1991 - [AD 91-15-20](https://openairdocs.org/ad/91-15-20): Engine Mount · Textron 58, 58A, 95-C55 and 5 more. Effective Sep 3, 1991 - [AD 90-08-14](https://openairdocs.org/ad/90-08-14): Wing Spar Structure · Textron 56TC, 58, 58A and 17 more. Effective May 7, 1990 - [AD 89-05-02](https://openairdocs.org/ad/89-05-02): Elevator Control Fittings · Textron 35, 35-33, 35-A33 and 42 more. Effective Mar 24, 1989 - [AD 88-21-02](https://openairdocs.org/ad/88-21-02): Seat Tracks · Textron 58, 58A, 58P and 13 more. Effective Oct 31, 1988 - [AD 87-18-06 R1](https://openairdocs.org/ad/87-18-06-R1): Seat Recline Actuator Handle · Textron 58, 58A, 58P and 9 more. Effective Feb 5, 1988 - [AD 87-16-11](https://openairdocs.org/ad/87-16-11): Placard -Icing · Textron 58. Effective Sep 1, 1987 - [AD 84-09-01](https://openairdocs.org/ad/84-09-01): Window Emergency Egress Provision · Textron 35, 36, 50 and 60 more. Effective May 25, 1984 - [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981 All 77: https://openairdocs.org/tcds/3A16/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Beech 95-B55 (T42A)](https://openairdocs.org/model/beech-95-b55-t42a): 774 aircraft (registry code 1152706) - [Beech 58](https://openairdocs.org/model/beech-58): 726 aircraft (registry code 1152740) - [Beech E-55](https://openairdocs.org/model/beech-e-55): 215 aircraft (registry code 1152732) - [Raytheon 58](https://openairdocs.org/model/raytheon-58): 188 aircraft (registry code 7150003) - [Beech 95-C55](https://openairdocs.org/model/beech-95-c55): 158 aircraft (registry code 1152708) - [Beech D55](https://openairdocs.org/model/beech-d55): 119 aircraft (registry code 1152730) - [Beech 95](https://openairdocs.org/model/beech-95): 95 aircraft (registry code 1153402) - [Beech 95-A55](https://openairdocs.org/model/beech-95-a55): 90 aircraft (registry code 1152704) - [Beech 95-B55](https://openairdocs.org/model/beech-95-b55): 74 aircraft (registry code 1152705) - [Beech D95A](https://openairdocs.org/model/beech-d95a): 73 aircraft (registry code 1153408) - [Hawker Beechcraft G58](https://openairdocs.org/model/hawker-beechcraft-g58): 67 aircraft (registry code 4220005) - [Textron G58](https://openairdocs.org/model/textron-g58): 59 aircraft (registry code 4220042) - [Beech B95](https://openairdocs.org/model/beech-b95): 54 aircraft (registry code 1153404) - [Beech 95-55](https://openairdocs.org/model/beech-95-55): 53 aircraft (registry code 1152702) - [Beech 56TC](https://openairdocs.org/model/beech-56tc): 37 aircraft (registry code 1152736) - [Beechcraft G58](https://openairdocs.org/model/beechcraft-g58): 35 aircraft (registry code 4220032) - [Beech B95A](https://openairdocs.org/model/beech-b95a): 32 aircraft (registry code 1153406) - [Raytheon G58](https://openairdocs.org/model/raytheon-g58): 25 aircraft (registry code 7150060) - [Beech E95](https://openairdocs.org/model/beech-e95): 6 aircraft (registry code 1153410) - [Beech A56TC](https://openairdocs.org/model/beech-a56tc): 3 aircraft (registry code 1152738) - [Beech 95-B55B (T42A)](https://openairdocs.org/model/beech-95-b55b-t42a): 0 aircraft (registry code 1152701) - [Boeing 95](https://openairdocs.org/model/boeing-95): 0 aircraft (registry code 1380095) - [Lark 95](https://openairdocs.org/model/lark-95): 0 aircraft (registry code 5160202) ## STCs approved under this data sheet (608, first 50) - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc. - [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA773CE](https://openairdocs.org/stc/SA773CE): Installation of Hartzell BHC- C2Y,BHC-J2Y, PHC-C3Y or PHC-J3Y propellers in accordance with Hartzell Manual 115G.. Hartzell Propeller LLC - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA01151CH](https://openairdocs.org/stc/SA01151CH): Installation of battery vent fairing with South Seas Ventures drawing, p/n 15627A, Rev 7, dtd 5/7/01, or later FAA approved revisions.. McFarlane Aviation LLC - [STC SA01152CH](https://openairdocs.org/stc/SA01152CH): Installation of stainless steel passenger step, P/N 002-430076-23, with South Seas Ventures, Inc. drawing as listed on AML No. SA01152CH, or later FAA approved revision.. McFarlane Aviation LLC - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA449CH](https://openairdocs.org/stc/SA449CH): Installation of a Traffic Alert and Collision Avoidance System,TCAS I (Model TCAS791/791A).. Acron Aviation Inc. - [STC SA01240SE](https://openairdocs.org/stc/SA01240SE): Installation of secondary voltage indication system. Visual Instruments LLC - [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA01120SE](https://openairdocs.org/stc/SA01120SE): Installation of Door Steward.. Mountain View Aviation LLC - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc. - [STC SA5902NM](https://openairdocs.org/stc/SA5902NM): Installation of locking fuel cap assembly. CheckSix AeroSolutions, LLC - [STC SA153SO](https://openairdocs.org/stc/SA153SO): Installation of Turbocharged Lycoming O-360-A1A, IO-360-B1A, or IO-360-B1B engines. TALCO Aviation - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA1827NM](https://openairdocs.org/stc/SA1827NM): Installation of Beech 95-E55 wings, fuel selector assembly, fuel gauges, and all related fuel couplings on a Beech 95-C55 aircraft. CheckSix AeroSolutions, LLC - [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC - [STC SA04537CH](https://openairdocs.org/stc/SA04537CH): Installation of wingtip position/anti-collision light support bracket. Gallagher Aviation LLC - [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC - [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc - [STC SA00803WI](https://openairdocs.org/stc/SA00803WI): Installation of a TKS Ice Protection System for approval of airplanes for Flight into Known Icing. CAV Ice Protection Inc. - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine - [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC - [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics - [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation - [STC SA04586CH](https://openairdocs.org/stc/SA04586CH): Installation of Electroair Back Up Battery Panel System Control. Electroair Aquisition Corp. - [STC SA00076IB](https://openairdocs.org/stc/SA00076IB): Installation of Photo luminescent Safety Systems. STG AEROSPACE GERMANY GmbH - [STC SA01830WI](https://openairdocs.org/stc/SA01830WI): G1000 Integrated Avionics System hardware and software updates including optional Flight Stream 510. Textron Aviation Inc. - [STC SA01422AT-D](https://openairdocs.org/stc/SA01422AT-D): Installation of Lower Cabin Door Stiffener. Summit Aviation Inc. - [STC SA19GL](https://openairdocs.org/stc/SA19GL): Install Cleveland 7.00-8 wheels and brakes.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA912GL](https://openairdocs.org/stc/SA912GL): Installation of Aircraft Wheel and Brake conversion kit199-138.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA01904WI](https://openairdocs.org/stc/SA01904WI): Installation of LED Position and Recognition Lights.. Whelen Aerospace Technologies - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA04580CH](https://openairdocs.org/stc/SA04580CH): Installation of the Nexus NX201001 air conditioning system in accordance with the Nexus Master Drawing List (MDL201001) and Installation Instructions (IN201001) as listed on AML No. SA04580CH. Airplane Flight Manual Supplement (AFMS201001) as listed on AML No. SA04580CH is required with this installation. The aircraft must be maintained in accordance with the FAA-accepted Instructions for Continued Airworthiness, (ICA201001) as listed on AML No. SA04580CH. Nexus Climate Control LLC All 608: https://openairdocs.org/tcds/3A16/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.